| preamble attached >>> |
ADs updated daily at www.Tdata.com
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| 2020-11-13 |
DE HAVILLAND AIRCRAFT OF CANADA LIMITED (TYPE CERTIFICATE
PREVIOUSLY HELD BY BOMBARDIER, INC.): Amendment 39-19917; Docket No. FAA-2020-0099; Product Identifier 2019-NM-169-AD. |
(a) EFFECTIVE DATE
This AD is effective July 14, 2020.
(b) AFFECTED ADS
This AD replaces AD 2010-23-04, Amendment 39-16493 (75 FR 68174,
November 5, 2010) ("AD 2010-23-04").
(c) APPLICABILITY
This AD applies to De Havilland Aircraft of Canada Limited (Type
Certificate previously held by Bombardier, Inc.) Model DHC-8-400,
-401, and -402 airplanes, certificated in any category, serial numbers
4001 and subsequent.
(d) SUBJECT
Air Transport Association (ATA) of America Code 54, Nacelles/pylons.
(e) REASON
This AD was prompted by reports of cracked nacelle attachment
fittings, which a preliminary investigation determined to be caused by
stress corrosion. The FAA is issuing this AD to address this
condition, which, if not detected and corrected, could compromise the
structural integrity of the nacelle attachment fitting and possibly
result in collapse of the landing gear.
(f) COMPLIANCE
Comply with this AD within the compliance times specified, unless al-
ready done.
(g) RETAINED DETAILED AND CONDUCTIVITY INSPECTIONS AND REPLACEMENT, WITH
REVISED SERVICE INFORMATION AND REVISED REPLACEMENT INSTRUCTIONS
This paragraph restates the requirements of paragraph (g) of AD 2010-
23-04, with revised service information and revised replacement
instructions. For airplanes having serial numbers 4001 through 4304
inclusive, 4314, and 4315: Within 100 flight hours after November 22,
2010 (the effective date of AD 2010-23-04), do a detailed inspection
for cracking, and a conductivity inspection on each of the 4 nacelle
attachment fittings, in accordance with the Accomplishment
Instructions of Bombardier Service Bulletin 84-54-14, Revision K,
dated August 7, 2018. Repeat the detailed inspection at intervals not
to exceed 300 flight hours, except as provided by paragraph (i) of
this AD. Accomplishing the replacement specified in paragraph
(g)(1)(ii) or (g)(2)(ii)(B) of this AD terminates the inspections re-
quired by this paragraph.
(1) If any nacelle attachment fitting is found cracked, before further
flight, do the action specified in paragraph (g)(1)(i) or (ii) of this
AD. As of the effective date of this AD, only the action specified in
paragraph (g)(1)(ii) of this AD may be done.
(i) Replace the fitting with a new fitting in accordance with paragraph
(2) of Part A of the Accomplishment Instructions of Bombardier Service
Bulletin 84-54-14, Revision K, dated August 7, 2018.
(ii) Replace the rear spar nacelle attachment fitting and associated
structure with a new nacelle attachment fitting, part number (P/N)
8Z9305, and do all applicable related investigative and corrective
actions, in accordance with Part B of the Accomplishment Instructions
of Bombardier Service Bulletin 84-54-16 Revision D, dated August 7,
2018. Do all applicable related investigative and corrective actions
before further flight.
(2) If the conductivity of any test points on any fitting is found to be
greater than 45.0 percent International Annealed Copper Standard
(IACS) or if the conductivity of any test points on any fitting is
found to be less than 38.0 percent IACS, do the actions required by
paragraphs (g)(2)(i) and (ii) of this AD.
(i) Within 24 hours after accomplishing the conductivity inspection speci-
fied in paragraph (g) of this AD, do a detailed inspection of the
nacelle attachment fitting for cracking, in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 84-54-14,
Revision K, dated August 7, 2018, and repeat thereafter at intervals
not to exceed 24 hours. If cracking is found, before further flight,
replace the fitting with a new fitting in accordance with the
requirements of paragraph (g)(2)(ii) of this AD. Replacement of the
fitting terminates the daily detailed inspection requirements of this
paragraph.
(ii) Except as required by paragraph (g)(2)(i) of this AD: Within 300
flight hours after accomplishing the conductivity inspection
specified in paragraph (g) of this AD, do the action specified in
paragraph (g)(2)(ii)(A) or (B) of this AD. As of the effective date
of this AD, only the action specified in paragraph (g)(2)(ii)(B) of
this AD may be done.
(A) Replace the fitting with a new fitting in accordance with paragraph
(2) of Part A of the Accomplishment Instructions of Bombardier Service
Bulletin 84-54-14, Revision K, dated August 7, 2018.
(B) Replace the rear spar nacelle attachment fitting and associated
structure with a new nacelle attachment fitting, P/N 8Z9305 and do all
applicable related investigative and corrective actions, in accordance
with Part B of the Accomplishment Instructions of Bombardier Service
Bulletin 84-54-16 Revision D, dated August 7, 2018. Do all applicable
related investigative and corrective actions before further flight.
(h) RETAINED INSPECTIONS AND REPLACEMENT WITH REVISED SERVICE INFORMATION,
REVISED AFFECTED AIRPLANES, AND REVISED REPLACEMENT INSTRUCTIONS
This paragraph restates the requirements of paragraph (i) of AD 2010-
23-04, with revised service information, revised affected airplanes,
and revised replacement instructions. For airplanes having serial
numbers 4305 through 4313 inclusive, and 4316 through 4380 inclusive,
and airplanes that have replaced nacelle attachment fitting(s) with
P/N 854146663: Within 1,200 flight hours after November 22, 2010 (the
effective date of AD 2010-23-04), do a detailed inspection for
cracking on each of the 4 nacelle attachment fittings, in accordance
with the Accomplishment Instructions of Bombardier Service Bulletin
84-54-14, Revision K, dated August 7, 2018. If any nacelle attachment
fitting is found cracked, before further flight, do the action
specified in paragraph (h)(1) or (2) of this AD. As of the effective
date of this AD, only the action specified in paragraph (h)(2) of this
AD may be done. Thereafter, repeat the detailed inspection at
intervals not to exceed 300 flight hours, except as provided by
paragraph (i) of this AD. Accomplishing the replacement specified in
paragraph (h)(2) of this AD terminates the inspections required by
this paragraph.
(1) Replace the fitting with a new fitting in accordance with paragraph
(2) of Part A of the Accomplishment Instructions of Bombardier Service
Bulletin 84-54-14, Revision K, dated August 7, 2018.
(2) Replace the rear spar nacelle attachment fitting and associated
structure with a new nacelle attachment fitting, P/N 8Z9305, and do
all applicable related investigative and corrective actions, in
accordance with Part B of the Accomplishment Instructions of
Bombardier Service Bulletin 84-54-16 Revision D, dated August 7, 2018.
Do all applicable related investigative and corrective actions before
further flight.
(i) RETAINED INSPECTION COMPLIANCE TIME, WITH REVISED SERVICE INFORMATION
This paragraph restates the requirements of paragraph (j) of AD 2010-
23-04, with revised service information. For any fitting that is
replaced in accordance with paragraph (3) of Part A of the
Accomplishment Instructions of Bombardier Service Bulletin 84-54-14,
Revision J, dated September 17, 2010; or paragraph (2) of Part A of
the Accomplishment Instructions of Bombardier Service Bulletin 84-54
-14, Revision K, dated August 7, 2018, as specified in paragraph (g)
or (h) of this AD: Within 1,200 flight hours after replacing the
fitting, do a detailed inspection of that replaced fitting as
specified in paragraph (g) or (h) of this AD, and repeat the detailed
inspection thereafter at intervals not to exceed 300 flight hours.
Accomplishing the replacement specified in paragraph (g)(1)(ii),
(g)(2)(ii)(B), or (h)(2) of this AD terminates the inspections
required by this paragraph.
(j) RETAINED CREDIT FOR PREVIOUS ACTIONS (REPLACING THE FITTING), WITH RE-
VISED PARAGRAPH REFERENCES
This paragraph restates the credit provided in paragraph (k) of AD
2010-23-04, with revised paragraph references. Accomplishing the
replacement of the nacelle fittings in accordance with any Bombardier
service bulletin identified in figure 1 to paragraphs (j) and (k) of
this AD before November 22, 2010 (the effective date of AD 2010-23-04)
is also acceptable for compliance with the fitting replacements
specified in paragraphs (g)(1)(i), (g)(2)(ii)(A), and (h)(1) of this
AD.
FIGURE 1 TO PARAGRAPHS (J) AND (K) – ACCEPTABLE SERVICE INFORMATION
______________________________________________________________________
BOMBARDIER SERVICE BULLETIN REVISION DATED
______________________________________________________________________
84-54-14 Original April 16, 2010
84-54-14 A April 22, 2010
84-54-14 B June 11, 2010
84-54-14 C June 30, 2010
84-54-14 D July 5, 2010
84-54-14 E August 19, 2010
84-54-14 F August 20, 2010
84-54-14 G September 9, 2010
84-54-14 H September 10, 2010
______________________________________________________________________
(k) RETAINED CREDIT FOR PREVIOUS ACTIONS (INSPECTIONS), WITH NO CHANGES
This paragraph restates the credit provided in paragraph (l) of AD
2010-23-04 with no changes. Accomplishment of the inspections required
by paragraphs (g) and (h) of this AD before November 22, 2010 (the
effective date of AD 2010-23-04) in accordance with any Bombardier
service bulletin identified in figure 1 to paragraphs (j) and (k) of
this AD is acceptable for compliance with the corresponding actions
required by paragraphs (g) and (h) of this AD.
(l) NEW REQUIREMENTS OF THIS AD: MODIFICATION OF THE REAR SPAR FITTING AND
NACELLE ATTACHING STRUCTURE
For airplanes with nacelle attachment fitting P/N 85414663: Unless al
- ready done as specified in paragraph (g)(1)(ii), (g)(2)(ii)(B), or
(h)(2) of this AD: Within 8,000 flight hours or 48 months, whichever
occurs first, from the effective date of this AD, replace the rear
spar nacelle attachment fitting and associated structure with a new
nacelle attachment fitting, P/N 8Z9305, and do all applicable related
investigative and corrective actions, in accordance with Part B of the
Accomplishment Instructions of Bombardier Service Bulletin 84-54-16,
Revision D, dated August 7, 2018. Do all applicable related
investigative and corrective actions before further flight.
(m) NEW CREDIT FOR PREVIOUS ACTIONS
(1) This paragraph provides credit for actions required by paragraphs (g)
and (h) of this AD that are identified in Bombardier Service Bulletin
84-54-14, Revision K, dated August 7, 2018, if those actions were
performed before the effective date of this AD using Bombardier
Service Bulletin 84-54-14, Revision J, dated September 17, 2010, which
was incorporated by reference in AD 2010-23-04; except as provided by
paragraph (p) of this AD.
(2) This paragraph provides credit for accomplishing the replacement of
the rear spar fitting and nacelle attaching structure required by
paragraph (l) of this AD, if those actions were performed before the
effective date of this AD using the service information specified in
paragraphs (m)(2)(i) through (iii) of this AD.
(i) Bombardier Service Bulletin 84-54-16, dated April 29, 2011.
(ii) Bombardier Service Bulletin 84-54-16, Revision A, dated August 1,
2011.
(iii) Bombardier Service Bulletin 84-54-16, Revision C, dated January 31,
2017.
(3) This paragraph provides credit for accomplishing the replacement of
the rear spar fitting and nacelle attaching structure required by
paragraph (l) of this AD, if those actions were performed before the
effective date of this AD using Bombardier Service Bulletin 84-54-16,
Revision B, dated October 6, 2016. Although Bombardier Service
Bulletin 84-54-16, Revision B, dated October 6, 2016, incorrectly
stated that airworthiness limitations (AWLs) or damage tolerance
inspections (DTIs) are not affected, they are affected. Refer to the
applicable AWLs for Post/Pre-Modification Summary (ModSum) 4-113697
and Bombardier Service Bulletin 84-54-16 in the existing maintenance
requirements manual.
(4) This paragraph provides credit for accomplishing the action identified
in Bombardier Service Bulletin 84-54-14, Revision K, dated August 7,
2018, that are required by paragraphs (g) and (h) of this AD, if those
actions were performed before the effective date of this AD using the
service information specified in paragraphs (m)(4)(i) through (iv) of
this AD.
(i) Bombardier Service Bulletin 84-54-15, dated August 20, 2010.
(ii) Bombardier Service Bulletin 84-54-15, Revision A, dated October 25,
2010. (iii) Bombardier Service Bulletin 84-54-15, Revision B, dated
February 2, 2017. (iv) Bombardier Service Bulletin 84-54-15, Revision
C, dated August 7, 2018.
(n) TERMINATING ACTION FOR CERTAIN ACTIONS IN PARAGRAPHS (G), (H), AND (I)
OF THIS AD
Accomplishing the modification of the rear spar fitting and nacelle
attaching structure required by paragraph (l) of this AD terminates
the repetitive inspection required by paragraphs (g), (h), and (i) of
this AD for that airplane.
(o) PARTS INSTALLATION LIMITATIONS
As of the effective date of this AD, no person may install a rear spar
nacelle attachment fitting P/N 85414663 on any airplane.
(p) CREDIT FOR ALTERNATIVE TO CERTAIN CREDIT ACTIONS
For airplanes on which Bombardier Service Bulletin 84-54-14, Revision
J, dated September 17, 2010, was accomplished before the effective
date of this AD: As an alternative to applying sealant to each fitting
and access panel as specified in paragraph C.(1) of the Accomplishment
Instructions of Bombardier Service Bulletin 84-54-14, Revision J,
dated September 17, 2010, the use of the instructions of Bombardier
Modification Summary Package IS4Q5400012, Revision B, dated July 11,
2012, to apply sealant is also acceptable if accomplished before the
effective date of this AD.
(q) OTHER FAA AD PROVISIONS
(1) Alternative Methods of Compliance (AMOCs): The Manager, New York 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 ATTN: Program Manager, Continuing Operational Safety, FAA, New
York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590;
telephone 516-228-7300; fax 516-794-5531.
(i) 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.
(ii) AMOCs approved previously for AD 2010-23-04, are approved as AMOCs
for the corresponding provisions of this AD.
(2) Contacting the Manufacturer: For any requirement in this AD to obtain
instructions from a manufacturer, the instructions must be
accomplished using a method approved by the Manager, New York ACO
Branch, FAA; or Transport Canada Civil Aviation (TCCA); or De
Havilland Aircraft of Canada Limited's TCCA Design Approval
Organization (DAO). If approved by the DAO, the approval must include
the DAO-authorized signature.
(r) RELATED INFORMATION
(1) Refer to Mandatory Continuing Airworthiness Information (MCAI)
Canadian AD CF-2010-30R2, dated July 30, 2019, for related
information. This MCAI may be found in the AD docket on the internet
at https://www.regulations.gov by searching for and locating Docket
No. FAA-2020-0099.
(2) For more information about this AD, contact Andrea Jimenez, Aerospace
Engineer, Airframe and Propulsion Section, FAA, New York ACO Branch,
1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-
7330; fax 516-794-5531; email 9-avs-nyaco-cos@faa.gov.
(3) Service information identified in this AD that is not incorporated by
reference is available at the addresses specified in paragraphs (s)(3)
and (4) of this AD.
(s) 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 this AD specifies otherwise.
(i) Bombardier Service Bulletin 84-54-14, Revision K, dated August 7, 2018
(ii) Bombardier Service Bulletin 84-54-16 Revision D, dated August 7, 2018
(iii) Bombardier Modification Summary Package IS4Q5400012, Revision B,
dated July 11, 2012.
(3) For service information identified in this AD, contact De Havilland
Aircraft of Canada Limited, Q-Series Technical Help Desk, 123 Garratt
Blvd., Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; fax
416-375-4539; email thd@dehavilland.com; internet https://dehavilland.
com.
(4) You may view this service information at the FAA, Airworthiness
Products Section, Operational Safety Branch, 2200 South 216th St., Des
Moines, WA. For information on the availability of this material at
the FAA, call 206-231-3195.
(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 May 29, 2020. Lance T Gant, Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
FOR FURTHER INFORMATION CONTACT: Andrea Jimenez, Aerospace Engineer, Air-
frame and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart Ave.,
Suite 410, Westbury, NY 11590; telephone 516-228-7330; fax 516-794-5531;
email 9-avs-nyaco-cos@faa.gov.
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