Airworthiness Directives; BAE Systems (Operations) Limited Airplanes

[Federal Register Volume 81, Number 156 (Friday, August 12, 2016)]
[Rules and Regulations]
[Pages 53252-53255]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-18821]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5465; Directorate Identifier 2015-NM-041-AD; 
Amendment 39-18609; AD 2016-16-11]
RIN 2120-AA64


Airworthiness Directives; BAE Systems (Operations) Limited 
Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2010-10-13, 
for all BAE Systems (Operations) Limited Model BAe 146 and Avro 146 
series airplanes. AD 2010-10-13 required repetitive inspections of the 
wing fixed leading edge and front spar structure for corrosion and 
cracking, and repair if necessary. This new AD requires revised 
inspection procedures that terminate a previously approved inspection 
procedure. This AD was prompted by revised inspection procedures issued 
by the Design Approval Holder (DAH). We are issuing this AD to detect 
and correct corrosion and cracking of the wing fixed leading edge and 
front spar structure, which could result in reduced structural 
integrity of the airplane.

DATES: This AD is effective September 16, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of September 
16, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of June 
21, 2010 (75 FR 27419, May 17, 2010).

ADDRESSES: For service information identified in this final rule, 
contact BAE Systems (Operations) Limited, Customer Information 
Department, Prestwick International Airport, Ayrshire, KA9 2RW, 
Scotland, United Kingdom; telephone +44 1292 675207; fax +44 1292 
675704; email [email protected]; Internet http://www.baesystems.com/Businesses/RegionalAircraft/index.htm. You may view 
this referenced service information at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the 
availability of this material at the FAA, call 425-227-1221. It is also 
available on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2016-5465.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
5465; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (telephone 800-
647-5527) is Docket Management Facility, 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: Todd Thompson, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1175; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2010-10-13, Amendment 39-16292 (75 FR 27419, 
May 17, 2010) (``AD 2010-10-13''). AD 2010-10-13 applied to all BAE 
Systems (Operations) Limited Model BAe 146 and Avro 146 series 
airplanes. The NPRM published in the Federal Register on April 20, 2016 
(81 FR 23208) (``the NPRM''). The NPRM was prompted by revised 
inspection procedures issued by the DAH. The NPRM proposed to continue 
to require repetitive inspections of the wing fixed leading edge and 
front spar structure for corrosion and cracking, and repair if 
necessary. The NPRM also proposed to require revised inspection 
procedures that terminate a previously approved inspection procedure. 
We are issuing this AD to detect and correct corrosion and cracking of 
the wing fixed leading edge and front spar structure, which could 
result in reduced structural integrity of the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0047; corrected February 26, 2015 
(referred to after this as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''); to correct an unsafe condition. The MCAI 
states:

    Corrosion of the wing fixed leading edge structure was detected 
on a BAe 146 aeroplane during removal of wing removable edge for a 
repair. The review of available scheduled tasks intended to detect 
environmental and fatigue deteriorations of the wing revealed that 
they may not have been sufficient to identify corrosion or fatigue 
damage in the affected structural area.
    This condition, if not detected and corrected, could lead to 
degradation of the structural integrity of the wing.
    To address this potential unsafe condition, EASA issued AD 2009-
0014 [which corresponds to FAA AD 2010-10-13] to require repetitive 
inspections of fixed wing leading edge and front spar structure [for 
cracking and corrosion, and repair if necessary] in accordance with 
BAE Systems (Operations) Ltd Inspection Service Bulletin (ISB) 
ISB.57-072 which incorporated two possible inspection procedures, 
either method 1, a combination of a detailed visual inspection (DVI) 
and a visual inspection (VI) after removal of the outer fixed 
leading edge only, or method 2, a DVI only, after removal of the 
inner, centre and outer fixed leading edges.
    Since that [EASA] AD was issued, BAE Systems (Operations) Ltd 
issued ISB.57-072 Revision 1 to correct a material reference number, 
Revision 2, which removed method 1 as an available inspection 
procedure to detect fatigue and environmental damage of the wing 
structure and Revision 3 to delete the requirement to install 
weights if the engines were removed when the leading edges were 
removed.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2009-0014, which is superseded, but requires 
accomplishment of the [repetitive] inspections in accordance with 
updated inspection procedures, i.e. method 2 only.
    This [EASA] AD is re-published to correct a typographical error 
in Table 1, restoring a compliance time as previously required by 
EASA AD 2009-0014.

    The repetitive inspection interval for the detailed visual 
inspection for cracking and corrosion of the wing fixed leading edge 
and front spar structure is:
    <bullet> 12 years or 36,000 flight cycles, whichever occurs 
earlier, for airplanes on which the enhanced corrosion protection has 
not been accomplished.
    <bullet> 6 years or 36,000 flight cycles, whichever occurs earlier, 
for airplanes on which the enhanced corrosion protection has been 
accomplished.
    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for

[[Page 53253]]

and locating Docket No. FAA-2016-5465.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    BAE Systems (Operations) Limited has issued Service Bulletin 
ISB.57-072, Revision 3, dated August 31, 2010. The service information 
describes procedures for inspection and repair for cracking and 
corrosion of the wing fixed leading edge and front spar structure. 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 the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 4 airplanes of U.S. registry.
    The actions required by AD 2010-10-13, and retained in this AD take 
about 12 work-hours per product, and 1 work-hour per product for 
reporting, at an average labor rate of $85 per work-hour. Based on 
these figures, the estimated cost of the actions that are required by 
AD 2010-10-13 is $1,105 per product.
    The new requirements of this AD add no additional economic burden.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to 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 control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is 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.

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.
    We are 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

    We 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. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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.

Adoption of 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

0
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]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2010-10-13, Amendment 39-16292 (75 FR 27419, May 17, 2010), and adding 
the following new AD:

2016-16-11 BAE Systems (Operations) Limited: Amendment 39-18609. 
Docket No. FAA-2016-5465; Directorate Identifier 2015-NM-041-AD.

(a) Effective Date

    This AD is effective September 16, 2016.

(b) Affected ADs

    This AD replaces AD 2010-10-13, Amendment 39-16292 (75 FR 27419, 
May 17, 2010) (``AD 2010-10-13'').

(c) Applicability

    This AD applies to BAE Systems (Operations) Limited Model BAe 
146-100A, -200A, and -300A series airplanes; and Model Avro 146-
RJ70A, 146-RJ85A, and 146-RJ100A airplanes; certificated in any 
category, all serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by revised inspection procedures issued by 
the Design Approval Holder. We are issuing this AD to detect and 
correct corrosion and cracking of the wing fixed leading edge and 
front spar structure, which could result in reduced structural 
integrity of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Actions and Compliance, With Added Provision for 
Terminating Action

    This paragraph restates the requirements of paragraph (f) of AD 
2010-10-13, with an added provision for terminating action. 
Accomplishing the initial inspection required by paragraph (j) of 
this AD terminates the requirements of paragraph (g) of this AD.
    (1) At the applicable time identified in paragraph (g)(1)(i), 
(g)(1)(ii), or (g)(1)(iii) of this AD: Perform a detailed visual 
inspection and visual inspection (Method 1) or a detailed visual 
inspection (Method 2) for cracking and corrosion of the wing fixed 
leading edge and front spar structure, in

[[Page 53254]]

accordance with paragraph 2.C. or 2.D., as applicable, of the 
Accomplishment Instructions of BAE Systems (Operations) Limited 
Inspection Service Bulletin ISB.57-072, Revision 1, dated September 
25, 2008.
    (i) For airplanes with less than 9 years since the date of 
issuance of the original airworthiness certificate or the date of 
issuance of the original export certificate of airworthiness as of 
the effective date of this AD: Within 18 months after June 21, 2010 
(the effective date of AD 2010-10-13).
    (ii) For airplanes with 9 years or more, but less than 15 years, 
since the date of issuance of the original airworthiness certificate 
or the date of issuance of the original export certificate of 
airworthiness as of June 21, 2010 (the effective date of AD 2010-10-
13): Within 18 months after June 21, 2010, or within 16 years since 
the date of issuance of the original airworthiness certificate or 
the date of issuance of the original export certificate of 
airworthiness, whichever occurs first.
    (iii) For airplanes with 15 years or more since the date of 
issuance of the original airworthiness certificate or the date of 
issuance of the original export certificate of airworthiness as of 
June 21, 2010 (the effective date of AD 2010-10-13): Within 6 months 
after June 21, 2010.
    (2) After doing the initial inspection required by paragraph 
(g)(1) of this AD, at the applicable intervals specified in 
paragraph (g)(2)(i) or (g)(2)(ii) of this AD, accomplish the 
repetitive inspections of the wing fixed leading edge and front spar 
structure for cracking and corrosion in the ``area of inspection'' 
specified in table 1 of paragraph 1.D., ``Compliance,'' of BAE 
Systems (Operations) Limited Inspection Service Bulletin ISB.57-072, 
Revision 1, dated September 25, 2008. Do the inspections in 
accordance with paragraph 2.C. (Method 1) or paragraph 2.D. (Method 
2) of the Accomplishment Instructions of BAE SYSTEMS (Operations) 
Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated 
September 25, 2008. Where previously applied, enhanced corrosion 
protection may then be re-applied, as an option, in accordance with 
paragraph 2.E. of the Accomplishment Instructions of BAE Systems 
(Operations) Limited Inspection Service Bulletin ISB.57-072, 
Revision 1, dated September 25, 2008. Perform the repetitive 
inspections at the times specified in paragraph (g)(2)(i) or 
(g)(2)(ii) of this AD, as applicable.
    (i) For airplanes having enhanced corrosion protection that was 
applied during the previous inspection: Inspect at intervals not to 
exceed 144 months.
    (ii) For airplanes not having enhanced corrosion protection that 
was applied during the previous inspection: Inspect at intervals not 
to exceed 72 months.
    (3) After doing the initial inspection required by paragraph 
(g)(1) of this AD, at intervals not to exceed 36,000 flight cycles, 
accomplish fatigue inspections in accordance with paragraph 2.C. 
(Method 1) or paragraph 2.D. (Method 2) of the Accomplishment 
Instructions of BAE Systems (Operations) Limited Inspection Service 
Bulletin ISB.57-072, Revision 1, dated September 25, 2008.
    (4) If any cracking or corrosion is found during any inspection 
required by paragraph (g) of this AD, before further flight, repair 
in accordance with the Accomplishment Instructions of BAE Systems 
(Operations) Limited Inspection Service Bulletin ISB.57-072, 
Revision 1, dated September 25, 2008.
    (5) No repair terminates the inspection requirements of this AD.
    (6) Actions done before June 21, 2010 (the effective date of AD 
2010-10-13), in accordance with BAE Systems (Operations) Limited 
Inspection Service Bulletin ISB.57-072, dated February 22, 2008, are 
considered acceptable for compliance with the corresponding actions 
specified in this AD.
    (7) Submit a report of the findings (both positive and negative) 
of the inspection required by paragraph (f)(1) of this AD to 
Customer Liaison, Customer Support (Building 37), BAE Systems 
(Operations) Limited, Prestwick International Airport, Ayrshire, KA9 
2RW, Scotland; fax +44 (0) 1292 675432; email 
[email protected], at the applicable time specified in 
paragraphs (g)(7)(i) and (g)(7)(ii) of this AD. The report must 
include the inspection results, a description of any discrepancies 
found, the airplane serial number, and the number of landings and 
flight hours on the airplane.
    (i) If the inspection was done on or after June 21, 2010 (the 
effective date of AD 2010-10-13): Submit the report within 30 days 
after the inspection.
    (ii) If the inspection was done before June 21, 2010 (the 
effective date of AD 2010-10-13): Submit the report within 30 days 
after June 21, 2010.

(h) Retained Corrosion Protection Information, With No Changes

    This paragraph restates the corrosion protection information in 
Note 2 of AD 2010-10-13, with no changes. At the discretion of the 
airplane owner/operator, corrosion protection may be embodied on 
those areas subject to a detailed visual inspection, in accordance 
with paragraph 2.E. or paragraph 2.F. of the Accomplishment 
Instructions of BAE Systems (Operations) Limited Inspection Service 
Bulletin ISB.57-072, Revision 1, dated September 25, 2008. 
Embodiment of enhanced corrosion protection in accordance with 
paragraph 2.E. of the Accomplishment Instructions of BAE Systems 
(Operations) Limited Inspection Service Bulletin ISB.57-072, 
Revision 1, dated September 25, 2008, allows the interval of the 
repetitive inspections (as required by paragraph (g)(2) of this AD) 
to be extended in the area(s) of application in accordance with 
paragraph (g)(2)(i) or (g)(2)(ii) of this AD, as applicable.

(i) Retained Inspection Information, With No Changes

    This paragraph restates the inspection information in Note 3 of 
AD 2010-10-13, with no changes. The inspections required by this AD 
prevail over the Maintenance Review Board Report (MRBR), Maintenance 
Planning Document (MPD), Corrosion Prevention and Control Program 
(CPCP), and Supplemental Structural Inspection Document (SSID) 
inspections defined in paragraph 1.C.(3) of BAE Systems (Operations) 
Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated 
September 25, 2008.

(j) New Requirement of This AD: Repetitive Inspection

    At the applicable time identified in paragraph (j)(1), (j)(2), 
or (j)(3) of this AD; or within 6 months after the effective date of 
this AD; whichever occurs later: Perform a detailed visual 
inspection for cracking and corrosion of the wing fixed leading edge 
and front spar structure, in accordance with paragraph 2.C. of the 
Accomplishment Instructions of BAE Systems (Operations) Limited 
Inspection Service Bulletin ISB.57-072, Revision 3, dated August 31, 
2010. Repeat the inspection thereafter at the applicable intervals 
specified in paragraph 1.D.2. of BAE Systems (Operations) Limited 
Inspection Service Bulletin ISB.57-072, Revision 3, dated August 31, 
2010. Accomplishing the initial inspection required by this 
paragraph terminates the requirements of paragraph (g) of this AD.
    (1) For airplanes with less than 9 years since the date of 
issuance of the original airworthiness certificate or the date of 
issuance of the original export certificate of airworthiness as of 
June 21, 2010 (the effective date of AD 2010-10-13): Within 18 
months after June 21, 2010, or within 9 years since the date of 
issuance of the original airworthiness certificate or the date of 
issuance of the original export certificate of airworthiness, 
whichever occurs later.
    (2) For airplanes with 9 years or more, but less than 15 years, 
since the date of issuance of the original airworthiness certificate 
or the date of issuance of the original export certificate of 
airworthiness as of June 21, 2010 (the effective date of AD 2010-10-
13): Within 18 months after June 21, 2010, or within 16 years since 
the date of issuance of the original airworthiness certificate or 
the date of issuance of the original export certificate of 
airworthiness, whichever occurs first.
    (3) For airplanes with 15 years or more since the date of 
issuance of the original airworthiness certificate or the date of 
issuance of the original export certificate of airworthiness as of 
June 21, 2010 (the effective date of AD 2010-10-13): Within 6 months 
after June 21, 2010.

(k) New Requirement of This AD: Repair

    If any crack or corrosion is found during any inspection 
required by paragraph (j) of this AD: Before further flight, repair 
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or the European Aviation 
Safety Agency (EASA); or BAE Systems (Operations) Limited's EASA 
Design Organization Approval (DOA).

(l) No Provisions for Terminating Action

    Accomplishment of any repair, as required by paragraph (k) of 
this AD, does not constitute terminating action for inspections 
required by this AD.

(m) Credit for Previous Actions

    This paragraph provides credit for actions required by this AD, 
if those actions were performed before the effective date of this AD

[[Page 53255]]

using BAE Systems (Operations) Limited Inspection Service Bulletin 
ISB.57-072, dated February 22, 2008; or BAE Systems (Operations) 
Limited Inspection Service Bulletin ISB.57-072, Revision 1, dated 
September 25, 2008.

(n) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Todd 
Thompson, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1175; fax 425-227-1149. Information 
may be emailed to: [email protected]. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the EASA; or BAE Systems (Operations) 
Limited's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required 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 5 
minutes 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.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-004; corrected February 26, 
2015; for related information. This MCAI may be found in the AD 
docket on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2016-5465.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (p)(5) and (p)(6) of this AD.

(p) 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.
    (3) The following service information was approved for IBR on 
September 16, 2016.
    (i) BAE Systems (Operations) Limited Inspection Service Bulletin 
ISB.57-072, Revision 3, dated August 31, 2010.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
June 21, 2010 (75 FR 27419, May 17, 2010).
    (i) BAE Systems (Operations) Limited Inspection Service Bulletin 
ISB.57-072, Revision 1, dated September 25, 2008.
    (ii) Reserved.
    (5) For service information identified in this AD, contact BAE 
Systems (Operations) Limited, Customer Information Department, 
Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United 
Kingdom; telephone +44 1292 675207; fax +44 1292 675704; email 
[email protected]; Internet http://www.baesystems.com/Businesses/RegionalAircraft/index.htm.
    (6) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (7) 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, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on July 27, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-18821 Filed 8-11-16; 8:45 am]
 BILLING CODE 4910-13-P

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