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ADs updated daily at www.Tdata.com
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| 2020-26-16 |
PIPER AIRCRAFT, INC.: Amendment 39-21371; Docket No. FAA-2018-1046; Product Identifier 2018-CE-049-AD. |
(a) EFFECTIVE DATE
This airworthiness directive (AD) is effective February 16, 2021.
(b) AFFECTED ADS
None.
(c) APPLICABILITY
This AD applies to Piper Aircraft Inc. (Piper) airplanes, certificated
in any category, with a model and serial number shown in table 1 to
paragraph (c) of this AD, and that meet at least one of the criteria
in paragraphs (c)(1), (2), or (3) of this AD.
Note 1 to the introductory text of paragraph (c): An owner / operator with
at least a private pilot certificate may do the aircraft maintenance
records review to determine the applicability as specified in paragraph
(c) of this AD.
(1) Has accumulated 5,000 or more hours time-in-service (TIS); or
(2) Has had either main wing spar replaced with a serviceable (more than
zero hours TIS) main wing spar; or
(3) Has missing and/or incomplete maintenance records.
TABLE 1 TO PARAGRAPH (C)
______________________________________________________________________
MODEL SERIAL NUMBERS
______________________________________________________________________
PA-28-151 All serial numbers
PA-28-161 All serial numbers except 2842006
PA-28-181 All serial numbers
PA-28-235 All serial numbers
PA-28R-180 All serial numbers
PA-28R-200 All serial numbers except 28R-7235151
PA-28R-201 All serial numbers except 2844029, 2844030, 2844081,
2844125, 2844136, 2844147 through 2844151,
28R-7737078, 28R-7737142, 28R-7837108, 28R-7837125,
and 28R-7837257
PA-28R-201T All serial numbers
PA-28RT-201 All serial numbers
PA-28RT-201T All serial numbers
PA-32-260 All serial numbers
PA-32-300 All serial numbers
PA-32R-300 All serial numbers
PA-32RT-300 All serial numbers except 32R-7985004
PA-32RT-300T All serial numbers
______________________________________________________________________
(d) SUBJECT
Joint Aircraft System Component (JASC) Code 5711, Wing Spar.
(e) UNSAFE CONDITION
This AD was prompted by a report of a wing separation caused by
fatigue cracking in a visually inaccessible area of the main wing
lower spar cap. The FAA is issuing this AD to detect and correct
fatigue cracks in the lower main wing spar cap bolt holes. The unsafe
condition, if not addressed, could result in the wing separating from
the fuselage in flight.
(f) COMPLIANCE
Comply with this AD within the compliance times specified, unless al-
ready done.
(g) DEFINITIONS
(1) "TIS" has the same meaning as the definition of "time in service" in
14 CFR 1.1.
(2) For purposes of this AD, "factored service hours" refers to the calcu-
lated quantity of hours using the formula in paragraph (h)(2) of this
AD, which accounts for the usage history of the airplane.
(h) REVIEW AIRPLANE MAINTENANCE RECORDS AND CALCULATE FACTORED SERVICE
HOURS FOR EACH MAIN WING SPAR
(1) Within 30 days after the effective date of this AD, review the air-
plane maintenance records and determine the number of 100-hour inspec-
tions completed on the airplane since new and any record of wing spar
replacement(s).
(i) For purposes of this review, count any inspection conducted to comply
with the 100-hour requirement of 14 CFR 91.409(b) pertaining to
carrying persons for hire, such as in-flight training environments,
even if the inspection was entered in the maintenance records as an
"annual" inspection or as an "annual/100-hour" inspection. If the
purpose of an inspection was to comply with §91.409(b), then it must
be counted. To determine the purpose of an inspection, note the
repeating intervals between inspections, i.e., less than 10 months
between, and typically 90-110 flight hours. An inspection entered as a
"100-hour" inspection but done solely for the purpose of meeting the
requirement to complete an annual inspection, or those otherwise not
required by §91.409(b), need not be counted. For operators utilizing a
progressive inspection program count the completion of each §91.409(b)
100-hour interval as one inspection.
(ii) If a main wing spar has been replaced with a new (zero hours TIS)
main wing spar, count the number of 100-hour inspections from the
time of installation of the new main wing spar.
(iii) If a main wing spar has been replaced with a serviceable main wing
spar (more than zero hours TIS) or the airplane maintenance records
are missing or incomplete, the wing history cannot be determined.
Perform the eddy current inspection as specified in paragraph (i) of
this AD.
(iv) The actions required by paragraph (h)(1) of this AD may be performed
by the owner/operator (pilot) holding at least a private pilot cer-
tificate and must be entered into the aircraft records showing com-
pliance with this AD in accordance with 14 CFR 43.9(a)(1) through (4)
and 14 CFR 91.417(a)(2)(v). The record must be maintained as required
by 14 CFR 91.417, 121.380, or 135.439.
(2) Before further flight after completing the action in paragraph (h)(1)
of this AD, calculate the factored service hours for each main wing
spar using the formula in figure 1 to paragraph (h)(2) of this AD.
Thereafter, after each annual inspection and 100-hour inspection,
recalculate/update the factored service hours for each main wing spar
until the main wing spar has accumulated 5,000 or more factored
service hours.
FIGURE 1 TO PARAGRAPH (H)(2)
______________________________________________________________________
N is the number of 100 - hour inspections and T is the total hours TIS
of the airplane.
[T-(N X 100)]
(N X 100) + ------------- = Factored Service Hours
17
______________________________________________________________________
(3) An example of determining factored service hours for an airplane with
no 100-hour inspections is as follows: The airplane maintenance
records show that the airplane has a total of 12,100 hours TIS, and
only annual inspections have been done. None of the annual inspections
were done for purposes of compliance with § 91.409(b). Both main wing
spars are original factory installed. In this case, N = 0 and T =
12,100. Use those values in the formula as shown in figure 2 to para-
graph (h)(3) of this AD. In the example in figure 2 to paragraph (h)
(3) of this AD), the eddy current inspection would not be required be-
cause the factored service hours are less than 5,000 hours.
FIGURE 2 TO PARAGRAPH (H)(3)
______________________________________________________________________
If the number of 100- hour inspections is 0 and the total hours TIS of
the airplane is 12,100 hours, then your formula would be:
[12,100 - (0 X 100)]
(0 X 100) + -------------------- = 711 Factored Service Hours
17
______________________________________________________________________
(4) An example of determining factored service hours for an airplane with
both 100-hour and annual inspections is as follows: The airplane was
originally flown for personal use, then for training for a period of
time, then returned to personal use. The airplane maintenance records
show that the airplane has a total of 10,600 hours TIS, and fifty-five
100-hour inspections for purposes of compliance with § 91.409(b) have
been done. Both main wing spars are original factory installed. In
this case, N = 55 and T = 10,600. Use those values in the formula
shown in figure 3 to paragraph (h)(4) of this AD. First, calculate
commercial use time by multiplying (N x 100). Next, subtract that time
from the total time, and divide that quantity by 17. Add the two
quantities to determine total factored service hours. In the example
in figure 3 to paragraph (h)(4) of this AD), the eddy current
inspection would be required because the factored service hours are
more than 5,000 hours.
FIGURE 3 TO PARAGRAPH (H)(4)
______________________________________________________________________
If the number of 100-hour inspections is 55 and the total hours TIS of
the airplane is 10,600 hours, then your formula would be:
[10,600 - (55 X 100)]
(55 X 100) + --------------------- =
17
[10,600 - (5,500)]
(5,500) + -------------------- =
17
(5,500) + 300 = 5,800 Factored Service Hours
______________________________________________________________________
(i) EDDY CURRENT INSPECT
Within the compliance time specified in either paragraph (i)(1) or (2)
of this AD, as applicable, eddy current inspect the inner surface of
the two lower outboard bolt holes on the lower main wing spar cap for
cracks. If the wing is installed, use steps 1 through 3 or, if the
wing is not installed, use step 3 in the Instructions of Piper
Aircraft, Inc. Service Bulletin No. 1345, dated March 27, 2020 (Piper
SB No. 1345). Although Piper SB No. 1345 specifies NAS 410 Level II or
Level III certification to perform the inspection, this AD allows
Level II or Level III qualification standards for inspection personnel
using any inspector criteria approved by the FAA.
Note 2 to the introductory text of paragraph (i): Advisory Circular 65-31B
contains FAA-approved Level II and Level III qualification standards
criteria for inspection personnel doing nondestructive test (NDT) inspec-
tions.
(1) Within 100 hours TIS after complying with paragraph (h) of this AD or
within 100 hours TIS after a main wing spar accumulates 5,000 factored
service hours, whichever occurs later; or
(2) For airplanes with an unknown number of factored service hours on a
main wing spar, within the next 100 hours TIS after the effective date
of this AD or within 60 days after the effective date of this AD,
whichever occurs later.
(j) REPLACE THE MAIN WING SPAR
If a crack is found during an inspection required by paragraph (i) of
this AD, before further flight, replace the main wing spar with a new
(zero hours TIS) main wing spar or with a serviceable (more than zero
hours TIS) main wing spar that has passed the eddy current inspection
required by paragraph (i) of this AD.
(k) INSTALL NEW BOLTS
Before further flight after completing the actions required by para-
graph (i) or (j) of this AD, install new bolts by following step 6 of
Piper Aircraft, Inc. Service Bulletin No. 1345, dated March 27, 2020.
(l) REPORT INSPECTION RESULTS
Within 30 days after completing an inspection required by paragraph
(i) of this AD, using Appendix 1, "Inspection Results Form," of this
AD, report the inspection results to the FAA at the Atlanta ACO Branch
and to Piper Aircraft. Submit the report to the FAA and Piper using
the contact information found on the form in appendix 1 of this AD.
(m) SPECIAL FLIGHT PERMIT
A special flight permit may only be issued to operate the airplane to
a location where the inspection requirement of paragraph (i) of this
AD can be performed. This AD prohibits a special flight permit if the
inspection reveals a crack in a main wing spar.
(n) PAPERWORK REDUCTION ACT BURDEN STATEMENT
A federal agency may not conduct or sponsor, and a person is not re-
quired to respond to, nor shall a person be subject to a penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a currently valid OMB Control Number. The OMB
Control Number for this information collection is 2120-0056. Public
reporting for this collection of information is estimated to be
approximately 1 hour per response, including the time for reviewing
instructions, searching existing data sources, gathering and
maintaining the data needed, completing and reviewing the collection
of information. All responses to this collection of information are
mandatory. Send comments regarding this burden estimate or any other
aspect of this collection of information, including suggestions for
reducing this burden to: Information Collection Clearance Officer,
Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth,
TX 76177-1524.
(o) 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 paragraph (p) of this AD.
(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.
(p) RELATED INFORMATION
For more information about this AD, contact Dan McCully, Aviation
Safety Engineer, Atlanta ACO Branch FAA, 1701 Columbia Avenue, College
Park, Georgia 30337; phone: (404) 474-5548; fax: (404) 474-5605; email
william.mccully@faa.gov.
(q) 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. 1345, dated March 27, 2020.
(ii) [Reserved]
(3) For Piper Aircraft, Inc. service information identified in this AD,
contact Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida
32960; phone: (772) 567-4361; website: https://www.piper.com.
(4) You may view this service information at FAA, Airworthiness Products
Section, Operational Safety Branch, 901 Locust, Kansas City, Missouri
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.
APPENDIX 1 TO AD 2020-26-16
__________________________________________________________________________
INSPECTION RESULTS FORM
Email completed form to: Or mail to: Federal Aviation Administration
9-ASO-ATLCOS-Reporting@faa.gov Atlanta ACO Branch, AIR-7A1
and 1701 Columbia Avenue
customer.service@piper.com College Park, GA 30337
and
SUBJECT line: Docket No. Piper Certification Office
FAA-2018-1046 2926 Piper Drive
Vero Beach, FL 32960
Include photos if applicable
Aircraft Model No.: PA- Serial Number:
Aircraft Total Hours
Time-In-Service (TIS): Registration Number:
Factored Service Hours
Left-Hand (LH) Wing: Right-Hand (RH) Wing:
(If both wings are factory installed original, these numbers should be the
same)
Inspection Results
LH Wing Spar Fwd RH Wing Spar Fwd
Accepted __ Rejected __ Accepted __ Rejected __
LH Wing Spar Aft RH Wing Spar Aft
Accepted __ Rejected __ Accepted __ Rejected __
Inspector Comments (observed damage, condition of hole, etc)
__________________________________________________________________________
__________________________________________________________________________
__________________________________________________________________________
__________________________________________________________________________
Inspector Information
Name (print): _______________________Signature: __________________________
Certificate No.: _________________________Date: __________________________
__________________________________________________________________________
Issued on December 30, 2020. Gaetano A. Sciortino, Deputy Director for
Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Cer-
tification Service.
FOR FURTHER INFORMATION CONTACT: Dan McCully, Aviation Safety Engineer,
Atlanta ACO Branch, FAA, 1701 Columbia Avenue, College Park, Georgia 30337
phone: (404) 474-5548; fax: (404) 474-5605; email: william.mccully@faa.gov
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DEPARTMENT OF TRANSPORTATION
The FAA estimates the following costs
to do the eddy current
The FAA estimates the following costs
to do any necessary
Paperwork Reduction Act |