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2020-18-01 |
TEXTRON AVIATION INC.: Amendment 39-21222; Docket No. FAA 2018-0049; Product Identifier 2017-CE-031-AD. |
(a) EFFECTIVE DATE
This AD is effective November 12, 2020.
(b) AFFECTED ADS
None.
(c) APPLICABILITY
This AD applies to the following Textron Aviation Inc. (type certifi-
cate previously held by Cessna Aircraft Company) model airplanes, cer-
tificated in any category:
TABLE 1 TO PARAGRAPH (C) OF THIS AD–AFFECTED MODELS AND SERIAL NUMBERS
______________________________________________________________________
MODEL SERIAL NUMBERS
______________________________________________________________________
172N 17272885 through 17274009 inclusive
172P All serial numbers
172Q 17275869, 17275927 through 17275934 inclusive,
17275952, 17275959, 17275960, 17275962, 17275964,
17275965, 17275967, 17275968, 17275969, 17275971,
17275992, 17275999, 17276002, 17276005, 17276029,
17276032, 17276042, 17276045, 17276051, 17276052,
17276054, 17276101, 17276109, 17276140, 17276147,
17276188, and 17276211
172RG All serial numbers
F172N F17201910 through F17202039 inclusive
F172P All serial numbers
FR172K FR17200656 through FR17200675 inclusive
R172K R1723200 through R1723454 inclusive
182E All serial numbers
182F All serial numbers
182G All serial numbers
182H All serial numbers
182J All serial numbers
182K All serial numbers
182L All serial numbers
182M All serial numbers
182N All serial numbers
182P All serial numbers
182Q All serial numbers
182R All serial numbers
T182 All serial numbers
F182P All serial numbers
F182Q All serial numbers
FR182 All serial numbers
R182 R18200002 through R18200583 inclusive
R182 and R18200001 and R18200584 through R18202039 inclusive
TR182
206 All serial numbers
P206, P206A, All serial numbers
P206B, P206C,
P206D, P206E,
TP206A, TP206B,
TP206C, TP206D,
and TP206E
U206, U206A, All serial numbers
U206B, U206C,
U206D, U206E,
U206F, U206G,
TU206A, TU206B,
TU206C, TU206D,
TU206E, TU206F,
and TU206G
207, 207A, All serial numbers
T207, and
T207A
210-5 (205) All serial numbers
210-5A (205A) All serial numbers
210B All serial numbers
210C All serial numbers
210D All serial numbers
210E All serial numbers
210F All serial numbers
T210F All serial numbers
______________________________________________________________________
(d) SUBJECT
Joint Aircraft System Component (JASC)/Air Transport Association (ATA)
of America Code 53, Fuselage.
(e) UNSAFE CONDITION
This AD was prompted by a report of cracks found in the lower area of
the forward cabin doorpost bulkhead. The FAA is issuing this AD to
detect and address cracking of the wing strut attach point. The unsafe
condition, if not addressed, could result in failure of the wing in
operation, which could result in loss of control of the airplane.
(f) COMPLIANCE
Comply with this AD within the compliance times specified, unless al-
ready done.
(g) INITIAL INSPECTIONS
(1) For airplanes without a lower forward doorpost bulkhead and wing strut
fitting reinforcement service kit (service kit) installed in
accordance with Cessna Single Engine Service Bulletin SEB95-19, dated
December 29, 1995 (SEB95-19), or Cessna Single Engine Service Bulletin
SEB93-5, Revision 2, dated May 29, 2019 (SEB93-5R2): At the applicable
compliance time specified in paragraph (g)(1)(i) or (ii) of this AD,
do a visual inspection of the lower forward doorpost at the strut
attach fitting for cracks in accordance with steps 1.A., 1.B., 1.C.,
and 1.B. (the step following step 1.C.) of the Accomplishment
Instructions in SEB95-19; or steps 1.A. and 1.B. of the Accomplishment
Instructions in SEB93-5R2; as applicable to your model airplane.
(i) For airplanes that have accumulated less than 4,000 hours time-in-
service (TIS) as of the effective date of this AD: Initially inspect
prior to the accumulation of 4,000 hours TIS or within the next 200
hours TIS after the effective date of this AD, whichever occurs later.
(ii) For airplanes that have accumulated 4,000 or more hours TIS as of the
effective date of this AD: Initially inspect within 200 hours TIS
after the effective date of this AD or within 12 calendar months
after the effective date of this AD, whichever occurs first.
(2) For airplanes with a service kit installed in accordance with SEB95-19
or SEB93-5R2: At the later of the times specified in paragraphs
(g)(2)(i) and (ii) of this AD, do a visual inspection of the lower
forward doorpost at the strut attach fitting for cracks in accordance
with steps 1.A., 1.B., 1.C., and 1.B. (the step following step 1.C.)
of the Accomplishment Instructions in SEB95-19; or steps 1.A. and 1.B.
of the Accomplishment Instructions in SEB93-5R2; as applicable to your
model airplane. Do not remove the installed service kit; instead,
inspect for cracking that extends beyond the modified parts.
(i) At the applicable time specified in paragraph (g)(1)(i) or (ii) of
this AD.
(ii) Within 1,000 hours TIS or 36 calendar months, whichever occurs first,
since installing the service kit.
(h) REPETITIVE INSPECTIONS
(1) If no cracks are found during the initial inspection required by para-
graph (g)(1) or (2) of this AD, thereafter repeat the inspection at
intervals not to exceed 36 calendar months or 1,000 hours TIS, which-
ever occurs first from the last inspection, as long as no cracks are
found.
(2) If cracks are found during any inspection required by paragraph (g)(1)
or (h)(1) of this AD, do the inspection specified in paragraph (g)(2)
of this AD within 36 calendar months or 1,000 hours TIS, whichever
occurs first after installing the service kit required by paragraph
(i)(1) of this AD. Thereafter, repeat the inspection at intervals not
to exceed 36 calendar months or 1,000 hours TIS, whichever occurs
first from the last inspection, as long as no additional cracks are
found.
(i) CORRECTIVE ACTIONS
(1) If cracks are found during any inspection required by paragraph (g)(1)
or paragraph (h)(1) of this AD, before further flight, install a serv-
ice kit in accordance with step 1.D. of the Accomplishment Instruc-
tions in SEB95-19; or step 1.C. of the Accomplishment Instructions in
SEB93-5R2; as applicable to your model airplane.
(2) If cracks are found during any inspection required by paragraph (g)(2)
or (h)(2) of this AD, before further flight, repair the area using a
method approved by the Manager, Wichita ACO Branch, FAA. For a repair
method to be approved by the Manager, Wichita ACO Branch as required
by this paragraph, the Manager's approval letter must specifically
refer to this AD. You may use the contact information in paragraph
(n)(1) of this AD to obtain FAA approval of your repair method.
(j) REPORTING REQUIREMENT
Within 30 days after the effective date of this AD, or within 30 days
after completing the initial inspection required by paragraph (g) of
this AD, whichever occurs later, report the findings of the initial
inspection (regardless if cracks were found or not) to the FAA at
Wichita-COS@faa.gov. Thereafter, within 30 days after completing each
repetitive inspection required by paragraph (h) of this AD, if any
crack was found, report the crack findings to the FAA at Wichita-COS@
faa.gov. Include in your reports the following information:
(1) Name and address of the owner;
(2) Date of the inspection;
(3) Name, address, telephone number, and email address of the person sub-
mitting the report;
(4) Airplane serial number and total hours TIS on the airplane at the time
of the inspection; and
(5) If any crack was found during the inspection, provide detailed crack
information as specified below:
(i) A sketch or picture detailing the crack location;
(ii) Measured length of the crack(s) found;
(iii) Installation of a Cessna service kit or any other kit or repair be-
fore the inspection; and
(iv) Installation of any supplemental type certificates (STCs), altera-
tions, repairs, or field approvals affecting the area of concern or
affecting gross weight.
(k) CREDIT FOR PREVIOUS ACTIONS
(1) You may take credit for the initial inspection required by paragraph
(g) of this AD if you performed the inspection before the effective
date of this AD using Cessna Single Engine Service Bulletin SEB93-5,
dated March 26, 1993; or Cessna Single Engine Service Bulletin SEB93-5
Revision 1, dated September 8, 1995.
(2) You may take credit for the installation required by paragraph (i)(1)
of this AD as follows.
(i) For Model 207, T207, 207A, and T207A airplanes with a service kit in-
stalled using SK206-42, SK206-42A, SK206-42B, or SK206-42C: You may
take credit for the installation if done before the effective date of
this AD using Cessna Single Engine Service Bulletin SEB93-5, dated
March 26, 1993, or Cessna Single Engine Service Bulletin SEB93-5,
Revision 1, dated September 8, 1995; if the reinforcement of the lower
forward doorpost bulkhead and wing strut fitting specified in Cessna
Single Engine Service Kit SK207-19A, dated May 29, 2019, is also
accomplished within 200 hours TIS after the effective date of this AD.
(ii) For all other models: You may take credit for the installation if
done before the effective date of this AD using Cessna Single Engine
Service Bulletin SEB93-5, dated March 26, 1993; or Cessna Single
Engine Service Bulletin SEB93-5, Revision 1, dated September 8, 1995.
(l) 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 current 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, completing and reviewing the collection of information.
All responses to this collection of information are mandatory.
Comments concerning the accuracy of this burden and suggestions for
reducing the burden should be directed to the FAA at: 800 Independence
Ave. SW, Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(m) ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)
(1) The Manager, Wichita 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 identi-
fied in paragraph (n)(1) 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.
(n) RELATED INFORMATION
(1) For more information about this AD, contact Bobbie Kroetch, Aerospace
Engineer, Wichita ACO Branch, 1801 Airport Road, Room 100, Wichita,
Kansas 67209; telephone: (316) 946-4155; fax: (316) 946-4107; email:
bobbie.kroetch@faa.gov or Wichita-COS@faa.gov.
(2) Service information identified in this AD that is not incorporated by
reference is available at the addresses specified in paragraphs (o)(3)
and (4) of this AD.
(o) MATERIAL INCORPORATED BY REFERENCE
(1) The Director of the Federal Register approved the incorporation by
reference (IBR) 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) Cessna Single Engine Service Bulletin SEB93-5, Revision 2, dated May
29, 2019.
(ii) Cessna Single Engine Service Bulletin SEB95-19, dated December 29,
1995.
(3) For service information identified in this AD, contact Textron
Aviation Inc., Textron Aviation Customer Service, One Cessna Blvd.,
Wichita, Kansas 67215; telephone: (316) 517-5800; email: customercare@
txtav.com; internet: https://support.cessna.com.
(4) You may view this service information at the 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
reference 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 August 24, 2020. Lance T Gant, Director, Compliance & Airworthi-
ness Division, Aircraft Certification Service.
FOR FURTHER INFORMATION CONTACT: Bobbie Kroetch, Aerospace Engineer,
Wichita ACO Branch, 1801 Airport Road, Room 100, Wichita, Kansas 67209;
telephone: (316) 946-4155; fax: (316) 946-4107; email: bobbie.kroetch@faa.
gov or Wichita-COS@faa.gov.
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DEPARTMENT OF TRANSPORTATION
The FAA estimates the following costs
to do any necessary repairs
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