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2021-11-16 PIPER AIRCRAFT, INC.: Amendment 39-21578; Docket No. FAA-2020-0881; Project Identifier 2018-CE-024-AD.
(a) EFFECTIVE DATE

    This airworthiness directive (AD) is effective July 15, 2021.

(b) AFFECTED ADS

    This AD replaces AD 79-01-03,  Amendment 39-3383 (44 FR 36, January 2,
    1979) (AD 79-01-03); and AD 83-20-03,  Amendment 39-4739 (48 FR 45535,
    October 6, 1983) (AD 83-20-03).

(c) APPLICABILITY

    This AD applies to Piper Aircraft, Inc. Models  PA-36-285,  PA-36-300,
    and PA36-375 airplanes, certificated in any category.

(d) SUBJECT

    Joint Aircraft System Component (JASC) Code 5700, Wings.

(e) UNSAFE CONDITION

    This AD was prompted  by a review of  AD 83-20-03 and AD  79-01-03 and
    the determination that the requirements  of those ADs did not  address
    all of the affected airplanes. The  FAA is issuing this AD to  prevent
    fatigue  damage  to  the   wing  structural  components.  The   unsafe
    condition,  if not  addressed,  could  result in  failure of  the wing
    structure with consequent loss of control.

(f) COMPLIANCE

    Comply with this AD within the compliance times specified,  unless al-
    ready done.

(g) INSPECTION OF THE WING SPAR CARRY THROUGH ASSEMBLY

(1) For Models PA-36-285 and PA-36-300 airplanes serial numbers 36-7360001
    through 36-7560003,  with a wing spar carry through assembly part num-
    ber (P/N) 97370-00 installed,  before the airplane accumulates a total
    of 2,000 hours time-in-service (TIS) or  within 25 hours TIS after the
    effective date of this AD, whichever occurs later,  and  thereafter at
    intervals  not to exceed 100 hours TIS,  inspect  the  wing spar carry
    through assembly  by following the Instructions, section 1,  of  Piper
    Service Bulletin No. 552A, dated August 3, 2018, (Piper SB No. 552A).

(2) If any damage is found during any inspection required by paragraph (g)
    (1) of this AD, before further flight, repair or replace the wing spar
    carry through assembly  by following the Instructions,  section 2,  of
    Piper SB No. 552A.

(3) Replacing wing spar carry through assembly P/N 97370-00 with wing spar
    carry through assembly  P/N 76824-02 terminates the repetitive inspec-
    tions required by paragraph (g)(1) of this AD.

(h) LIFE LIMIT REPLACEMENT OF WING STRUCTURAL COMPONENTS

    Remove  from  service  the  wing  structural  components  specified in
    paragraphs (h)(1) through (8) of  this AD before the part  accumulates
    the life limit hours TIS set forth in table 1 to paragraph (h) of this
    AD. If, on the effective date of this AD, the component will reach its
    life limit within 100 hours TIS or has already reached its life limit,
    remove the part from service within 100 hours TIS after the  effective
    date of this AD.

TABLE 1 TO PARAGRAPH (H)   COMPLIANCE TIMES FOR LIFE LIMIT REPLACEMENT OF
                            WING COMPONENTS                               
__________________________________________________________________________
AIRPLANES     TYPE OF                    PARAGRAPH OF THIS AD
            REPLACEMENT
__________________________________________________________________________
                            (h)(1)  (h)(4)  (h)(5)  (h)(6)  (h)(7)  (h)(8)
                            (h)(2)
                            (h)(3)
__________________________________________________________________________
MODELS PA-36-285 AND               LIFE LIMIT HOURS TIME-IN-SERVICE
PA-36-300                                  ON THE COMPONENT
__________________________________________________________________________
Serial       Initial        4,100   4,100   N/A     N/A     3,100   2,000
Numbers      Repetitive     4,100   4,100   N/A     N/A     4,100   2,000
(S/Ns)
36-7360001
through
36-7560003

S/Ns         Initial        4,100   N/A     N/A     4,000   3,100   2,000
36-7560004   Repetitive     4,100   N/A     N/A     4,100   4,100   2,000
through
36-7560055

S/Ns         Initial        4,100   N/A     4,100   4,100   N/A     2,000
36-7560056   Repetitive     4,100   N/A     4,100   4,100   N/A     2,000
through
36-7660122

S/Ns         Initial        4,100   4,100   4,100   N/A     N/A     2,000
36-7660123   Repetitive     4,100   4,100   4,100   N/A     N/A     2,000
through
36-8160023
__________________________________________________________________________
MODEL PA-36-375                    LIFE LIMIT HOURS TIME-IN-SERVICE
                                           ON THE COMPONENT
__________________________________________________________________________
                            (h)(1)  (h)(4)  (h)(5)  (h)(6)  (h)(7)  (h)(8)
                            (h)(2)
                            (h)(3)

S/Ns         Initial        4,100   4,100   4,100   N/A     N/A     2,000
36-7802001   Repetitive     4,100   4,100   4,100   N/A     N/A     2,000
through
36-8302025
__________________________________________________________________________

(1) Remove from service wing attachment upper bolt  P/N 77245-00  and  re-
    place with an unused (zero hours TIS)  wing attachment  upper bolt P/N
    77245-00.

(2) Remove from service any wing carry through spar fitting P/Ns 97713-00,
    97713-02, or 97713-03 and replace with an unused (zero hours TIS) wing
    carry through spar fitting P/N 97713-03.

Note 1 to paragraph (h)(2):  Wing carry through spar fitting  P/N 97713-03
is included as part of spar carry through assembly P/N 76824-02.

(3) Remove from service wing spar fitting P/N 97712-00 and replace with an
    unused (zero hours TIS) wing spar fitting  P/N 97712-00  by  following
    steps D(1)(a) through D(1)(c) or section D(2) in Piper Aircraft PA-36,
    Pawnee Brave Kit 764-393, Left Wing Main Spar Caps Replacement,  dated
    June 9, 2012 (Piper Kit 764-393) or Piper Aircraft PA-36, Pawnee Brave
    Kit 764-394, Right Wing Main Spar Caps Replacement, dated June 9, 2012
    (Piper Kit 764-394), as applicable.

Note 2 to paragraphs (h)(3):  This note  applies  to paragraphs (h)(3) and
(7) of this AD.  Replacement parts  for the left and right wing spar fitt-
ings P/N 97712-00 and the right, left, top and bottom spar assemblies P/Ns
97701-00 and 97701-01  are included  with  Piper Kit 764-393 and Piper Kit
764-394.

(4) Remove from service spar carry through assembly P/N 97370-00 or 76824-
    02, as applicable,  and  replace  with an unused (zero hours TIS) spar
    carry through assembly P/N 76824-02.

(5) Remove from service spar assembly P/Ns 97701-00 and 97701-01, Revision
    P or later revision,  and replace with an unused (zero hours TIS) spar
    assembly by following the Instructions,  sections B. and C.,  in Piper
    Kit 764-393 or Piper Kit 764-394, as applicable.

(6) Remove from service  any  spar carry through assembly  P/N 76767-00 or
    P/N 76824-02  and  replace  with an unused (zero hours TIS) spar carry
    through assembly P/N 76824-02.

(7) Remove  from  service  spar  assemblies  P/Ns  97701-00  and 97701-01,
    Revision N or earlier revision, and replace with an unused (zero hours
    TIS) left spar cap replacement kit  P/N 764-393 and right spar cap re-
    placement kit P/N 764-394  by following the Instructions,  sections B.
    and C., in Piper Kit 764-393 or Piper Kit 764-394, as applicable.

(8) Remove from service  wing attachment  lower bolt  P/N 77245-00 and re-
    place with an unused (zero hours TIS) P/N 77245-00 bolt.

(i) CREDIT FOR PREVIOUS ACTIONS

    You may take credit for the actions required by paragraph (g) of  this
    AD if you performed those actions before the effective date of this AD
    using  Piper Aircraft Corporation  Service  Bulletin  No.  552,  dated
    February 3, 1978.

(j) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)

(1) The  Manager,  Atlanta ACO Branch,  FAA,  has the authority to approve
    AMOCs for this AD, if requested  using the procedures found in 14  CFR
    39.19. In  accordance with  14 CFR  39.19, send  your request  to your
    principal  inspector  or  local Flight  Standards District  Office, as
    appropriate. If  sending information  directly to  the manager  of the
    certification  office,  send  it  to  the  attention  of  the   person
    identified in Related Information.

(2) Before using any approved AMOC,  notify your appropriate principal in-
    spector, or lacking  a principal inspector,  the manager of  the local
    flight standards district office/certificate holding district office.

(3) AMOCs approved for AD 79-01-03  and  AD 83-20-03 are approved as AMOCs
    for the corresponding provisions of this AD.

(k) RELATED INFORMATION

    For  more  information about this AD,  contact  Dan McCully,  Aviation
    Safety Engineer, FAA Atlanta ACO Branch, 1701 Columbia Avenue, College
    Park, GA 30337;  phone: (404) 474-5548;  fax:  (404) 474-5606;  email:
    william.mccully@faa.gov.

(l) MATERIAL INCORPORATED BY REFERENCE

(1) The Director of the Federal Register  approved  the  incorporation  by
    reference of the service information listed  in this paragraph under 5
    U.S.C. 552(a) and 1 CFR part 51.

(2) You must use  this service information as applicable to do the actions
    required by this AD, unless the AD specifies otherwise.

(i) Piper Service Bulletin No. 552A, dated August 3, 2018;

(ii) Piper Aircraft PA-36, Pawnee Brave Kit 764-394,  Right Wing Main Spar
     Caps Replacement, dated June 9, 2012; and

Note 3 to paragraph (l)(2)(ii):  The Kit List and Sketch A  for Piper Air-
craft PA-36, Pawnee Brave Kit 764-394,  Right Wing Main Spar Caps Replace-
ment, dated June 9, 2012; and Piper Aircraft PA-36,  Pawnee Brave Kit 764-
393, Left Wing Main Spar Caps Replacement dated June 9, 2012, were revised
and dated June 9, 2012.  The instructions and sketches  in the rest of the
documents were reformatted but retain the previous date of March 30, 1982,
because the content of those pages was unchanged.

(iii) Piper Aircraft PA-36, Pawnee Brave Kit 764-393,  Left Wing Main Spar
      Caps Replacement, dated June 9, 2012.

(3) For service information identified in this AD, contact Piper Aircraft,
    Inc.,  2926 Piper Drive, Vero Beach, FL 32960;  phone: (772) 567-4361;
    website: www.piper.com.

(4) You may view this service information at FAA,  Policy  and  Innovation
    Division,  901 Locust,  Kansas City, MO 64106.  For information on the
    availability of this material at the FAA, call (816) 329-4148.

(5) You may view this service information  that is incorporated  by refer-
    ence at the National  Archives and Records Administration  (NARA). For
    information  on  the availability  of  this material  at  NARA, email:
    fedreg.legal@nara.gov,  or  go  to:  https://www.archives.gov/federal-
    register/cfr/ibr-locations.html.

Issued on May 19, 2021. Lance T Gant, Director, Compliance & Airworthiness
Division, Aircraft Certification Service.

FOR FURTHER INFORMATION CONTACT: Dan McCully,  Aviation  Safety  Engineer,
FAA,  Atlanta ACO Branch,  1701 Columbia Avenue,  College Park, GA  30337;
phone: (404) 474-5548; fax: (404) 474-5606; email william.mccully@faa.gov.
PREAMBLE 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0881; Project Identifier 2018-CE-024-AD; Amendment
39-21578; AD 2021-11-16]
RIN 2120-AA64

Airworthiness Directives; Piper Aircraft, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 79-01-03,
which applied to certain Piper Aircraft, Inc. (Piper) Model PA-36-285
airplanes, and AD 83-20-03, which applied to Piper Models PA-36-285,
PA-36-300, and PA-36-375 airplanes. AD 79-01-03 required repetitive
inspections of the spar carry through assembly until replaced with a
different part numbered spar carry through assembly. AD 83-20-03
established life limits for the wing spar structural components. This
AD retains the requirements in AD 79-01-03 and AD 83-20-03 and requires
the spar carry through assembly inspection from AD 79-01-03 for
additional airplanes and adds life limits for certain wing structural
components previously omitted from AD 83-20-03 for certain serial
numbered airplanes. The FAA is issuing this AD to address the unsafe
condition on these products.

DATES: This AD is effective July 15, 2021.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of July 15,
2021.

ADDRESSES: For service information identified in this final rule,
contact Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, FL 32960;
phone: (772) 567-4361; website: https://www.piper.com. You may view
this service information at the FAA, Airworthiness Products Section,
Operational Safety Branch, 901 Locust, Kansas City, MO 64106. For
information on the availability of this material at the FAA, call (816)
329-4148. It is also available at https://www.regulations.gov by
searching for and locating Docket No. FAA-2020-0881.

Examining the AD Docket

You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2020-0881; or in person at
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket contains this final rule, any
comments received, and other information. The address for Docket
Operations is U.S. Department of Transportation, Docket Operations, M-
30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue
SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Dan McCully, Aviation Safety Engineer,
FAA, Atlanta ACO Branch, 1701 Columbia Avenue, College Park, GA 30337;
phone: (404) 474-5548; fax: (404) 474-5606; email:
william.mccully@faa.gov.

SUPPLEMENTARY INFORMATION:

Background

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 79-01-03, Amendment 39-3383 (44 FR 36,
January 2, 1979), Docket No. 78-EA-69 (AD 79-01-03) and AD 83-20-03,
Amendment 39-4739 (48 FR 45535, October 6, 1983), Docket No. 83-CE-23-
AD (AD 83-20-03). AD 79-01-03 applied to certain Piper Model PA-36-285
airplanes and required repetitive inspections of spar carry through
assembly part number (P/N) 97370-00, with repair as necessary, until
the spar carry through assembly is replaced with P/N 76824-02. AD 83-
20-03 applied to Piper Models PA-36-285, PA-36-300, and PA-36-375
airplanes and established life limits for certain wing structural
components.
The NPRM published in the Federal Register on March 23, 2021 (86 FR
15439). The NPRM was prompted by inconsistencies between the two ADs
and the airplanes' type certificate. The FAA determined that the life
limits for the spar carry through assembly, P/N 97370-00 or 76824-02,
were inadvertently omitted from AD 83-20-03 for certain airplanes. In
the NPRM, the FAA proposed to add the life limit for the spar carry
through assembly for Models PA-36-285 and PA-36-300 airplanes, serial
numbers 36-7660123 through 36-8160023; and Model PA-36-375 airplanes,
serial numbers 36-7802001 through 36-8302025. The FAA also determined
the repetitive inspections of the spar carry through assembly required
by AD 79-01-03 should apply to both Model PA-36-285 and Model PA-36-300
airplanes until the life limit replacement of the spar carry through
assembly with P/N 76824-02. In the NPRM, the FAA also proposed to
require adding the repetitive inspections for the Model PA-36-300
airplanes. After the initial life limit replacement of the wing spar
carry through assembly, P/N 97370-00 with P/N 76824-02, the repetitive
inspections will no longer be required.
The FAA is issuing this AD to address the unsafe condition on these
products.

Discussion of Final Airworthiness Directive

Comments

The FAA received no comments on the NPRM or on the determination of
the costs.

Conclusion

The FAA reviewed the relevant data and determined that air safety
requires adoption of the AD as proposed. Accordingly, the FAA is
issuing this AD to address the unsafe condition on these products. This
AD is adopted as proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

The FAA reviewed Piper Service Bulletin No. 552A, dated August 3,
2018 (Piper SB No. 552A); Piper Aircraft PA-36, Pawnee Brave Kit 764-
394, Right Wing Main Spar Caps Replacement, dated June 9, 2012 (Piper
Kit 764-394); and Piper Aircraft PA-36, Pawnee Brave
Kit 764-393, Left Wing Main Spar Caps Replacement, dated June 9, 2012
(Piper Kit 764-393). Piper SB No. 552A applies to Models PA-36-285 and
PA-36-300 airplanes and contains procedures for repetitively inspecting
wing spar carry through assembly P/N 97370-00. Piper Kit 764-394
identifies the applicable parts and specifies procedures for replacing
the right wing main spar caps, which includes the attachment bolts and
wing carry through spar fittings and assembly. Piper Kit 764-393
identifies the applicable parts and specifies procedures for replacing
the left wing main spar caps, which includes the attachment bolts and
wing carry through spar fittings and assembly. This service information
is reasonably available because the interested parties have access to
it through their normal course of business or by the means identified
in ADDRESSES.

Other Related Service Information

The FAA also reviewed Piper Aircraft Corporation Service Bulletin
No. 552, dated February 3, 1978 (Piper SB No. 552). Piper SB No. 552
contains the same procedures as Piper SB No. 552A, but Piper SB No. 552
only applies to Model PA-36-285 airplanes.

Costs of Compliance

The FAA estimates that this AD will affect 123 airplanes of U.S. registry.
The FAA estimates the following costs to comply with this AD:

Estimated Costs

Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspection of P/N 97370-00 wing spar carry through assembly 8 work-hours x $85 per hour = $680 Not applicable $680 $83,640
Replacement of the wing attachment upper bolt and lower bolt 10 work-hours x $85 per hour = $850 $1,310 (both bolts) 2,160 265,680
Replacement of wing carry through spar assembly * 30 work-hours x $85 per hour = $2,550 $23,467 26,017 3,200,091
Replacement of Piper Kit 764-393 (Left) and Piper Kit 764-394 (Right) ** 20 work-hours x $85 per hour = $1,700 $26,867 (both kits) 28,567 3,513,741

* The wing carry through spar fitting, P/N 97713-03, is included in the wing carry
through spar assembly, P/N 76824-02.
** The replacement for the wing spar fitting P/N 97712-00 and the replacement
for spar assembly P/Ns 97701-00 and 97701-01 are included in Piper Kit 764-393
and Piper Kit 764-394.

Authority for This Rulemaking


Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.

Regulatory Findings


The FAA has determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

The Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by:

a. Removing Airworthiness Directive 79-01-03, Amendment 39-3383 (44 FR
36, January 2, 1979), Docket No. 78-EA-69; and Airworthiness Directive
83-20-03, Amendment 39-4739 (48 FR 45535, October 6, 1983), Docket No.
83-CE-23-AD; and

b. Adding the following new airworthiness directive: