Document ID: FAA-2016-9186-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: BAE Systems (Operations) Limited
Posted Date: 2016-10-20T04:00Z

[Federal Register Volume 81, Number 203 (Thursday, October 20, 2016)]
[Proposed Rules]
[Pages 72557-72561]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-24201]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9186; Directorate Identifier 2015-NM-160-AD]
RIN 2120-AA64

Airworthiness Directives; BAE Systems (Operations) Limited

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2012-16-
08, for certain BAE Systems (Operations) Limited Model BAe 146 and Avro 
146-RJ series airplanes. AD 2012-16-08 currently requires repetitive 
detailed inspections for bulging, surface anomalies, and cracking of 
the fuselage skin adjacent to the discharge valves, and repair and 
application of additional sealant in the affected area if necessary. 
Since we issued AD 2012-16-08, it was found that airplanes on which a 
certain modification was incorporated during production were excluded 
from the applicability, but are also affected by the condition that 
precipitated AD 2012-16-08. This proposed AD would retain the 
requirements of AD 2012-16-08, expand the applicability, and require an 
additional one-time inspection for the presence of water traps/air 
driers to determine which airplanes must be inspected. We are proposing 
this AD to detect and correct bulging, surface anomalies, and cracking 
that could propagate towards the forward discharge valve outlet and 
result in the failure of the fuselage skin, leading to a possible 
sudden loss of cabin pressure and injury to occupants.

DATES: We must receive comments on this proposed AD by December 5, 
2016.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.

[[Page 72558]]

    For service information identified in this NPRM, 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 
RApublications@baesystems.com; 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.

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-
9186; 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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Theodore 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: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-9186; 
Directorate Identifier 2015-NM-160-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On July 31, 2012, we issued AD 2012-16-08, Amendment 39-17155 (77 
FR 48420, August 14, 2012) (``AD 2012-16-08''). AD 2012-16-08 requires 
repetitive detailed inspections for bulging, surface anomalies, and 
cracking of the fuselage skin adjacent to the discharge valves, and 
repair and application of additional sealant in the affected area if 
necessary.
    Since we issued AD 2012-16-08, it was found that airplanes that 
have incorporated auto-pressurization modification No. HCM50259A during 
production, which were excluded from the applicability, are also 
affected by this condition. In addition, and in order to simplify 
instructions and determine affected airplanes, BAE Systems (Operations) 
Limited issued BAE Systems (Operations) Limited Inspection Service 
Bulletin ISB.21-162, Revision 4, dated January 28, 2015, introducing a 
one-time inspection to determine if water trap/air driers are 
installed.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0180, dated August 28, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all BAE Systems 
(Operations) Limited Model BAe 146 series airplanes and Model Avro 146-
RJ series airplanes. The MCAI states:

    An operator reported finding cracking and surface anomalies 
(bulges and/or dents) of the fuselage skin at the water trap/air 
drier unit of the forward discharge valve, located between fuselage 
frame (FR) 22 and FR23 and between stringers 22 and 23. Further 
investigation established that these surface anomalies were due to 
corrosion beneath the water trap/air drier unit that has resulted in 
cracking of the fuselage skin
    This condition, if not detected and corrected, could lead to 
failure of the fuselage skin, possibly resulting in loss of cabin 
pressure and injury to occupants.
    To address this potential unsafe condition, EASA issued AD 2011-
0099 [which corresponds to FAA AD 2012-16-08] to require repetitive 
detailed visual inspections (DVI) of the fuselage skin adjacent to 
the front and rear discharge valves to check for bulging, surface 
anomalies and cracking, and, depending on findings, accomplishment 
of applicable corrective action(s), and the application of 
additional sealant in the affected area.
    Since that [EASA] AD was issued, it was found that aeroplanes 
that have incorporated auto-pressurisation modification No. 
HCM50259A during production, which were excluded from the 
Applicability, were also affected by this condition.
    In addition, and in order to simplify instructions for 
applicability, BAE Systems (Operations) Limited issued Revision 4 of 
Inspection Service Bulletin (ISB) No. 21-162, introducing a one-time 
inspection to identify if water trap/air driers are installed.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2011-0099, which is superseded, expands the 
Applicability and requires the additional one-time inspection as 
specified in the latest ISB revision.
    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9186.

Related Service Information Under 1 CFR Part 51

    BAE Systems (Operations) Limited has issued BAE Systems 
(Operations) Limited Service Bulletin ISB.21-162, Revision 4, dated 
January 28, 2015. The service information describes procedures for a 
visual inspection of the internal fuselage at the location of the water 
trap/air driers to determine if water trap/air driers are installed; an 
external DVI for bulging, surface anomalies, and cracking of the 
fuselage skin adjacent to the forward and rear discharge valve outlets; 
repair; and sealant application.
    BAE Systems (Operations) Limited has also issued the following 
service information, which describes procedures for structural repairs.
     Subject 53-00-00, ``Fuselage, General Description,'' of 
Chapter 53, ``Fuselage,'' of the BAE SYSTEMS BAe 146 Series/AVRO 146-RJ 
Series Structural Repair Manual for Series 100-200, Revision 68, dated 
October 15, 2014.
     Subject 53-00-00, ``Fuselage, General Description,'' of 
Chapter 53, ``Fuselage,'' of the BAe SYSTEMS BAE 146 Series/AVRO 146-RJ 
Series Structural Repair Manual for Series 300, Revision 46, dated 
October 15, 2014.
    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.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or

[[Page 72559]]

develop on other products of these same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 4 airplanes of U.S. 
registry.
    The actions required by AD 2012-16-08 and retained in this proposed 
AD take about 8 work-hours per product, at an average labor rate of $85 
per work-hour. Required parts cost about $0 per product. Based on these 
figures, the estimated cost of the actions that are required by AD 
2012-16-08 is $680 per product.
    We also estimate that it would take about 8 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $2,720, or $680 
per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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) 
2012-16-08, Amendment 39-17155 (77 FR 48420, August 14, 2012), and 
adding the following new AD:

BAE Systems (Operations) Limited: Docket No. FAA-2016-9186; 
Directorate Identifier 2015-NM-160-AD.

(a) Comments Due Date

    We must receive comments by December 5, 2016.

(b) Affected ADs

    This AD replaces AD 2012-16-08, Amendment 39-17155 (77 FR 48420, 
August 14, 2012) (``AD 2012-16-08'').

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, certificated in any category, all serial 
numbers.
    (1) BAE Systems (Operations) Limited Model BAe 146-100A, -200A, 
and -300A airplanes.
    (2) BAE Systems (Operations) Limited Model Avro 146-RJ70A, 146-
RJ85A, and 146-RJ100A airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 21, Air 
Conditioning.

(e) Reason

    This AD was prompted by reports of cracking and surface 
anomalies of the fuselage skin at the water trap/air drier unit of 
the forward discharge valve due to corrosion, and the determination 
that airplanes on which auto-pressurization modification No. 
HCM50259A was incorporated during production were excluded from the 
applicability of AD 2012-16-08, but are also affected by this 
condition. We are issuing this AD to detect and correct bulging, 
surface anomalies, and cracking that could propagate towards the 
forward discharge valve outlet and result in the failure of the 
fuselage skin, leading to a possible sudden loss of cabin pressure 
and injury to occupants.

(f) Compliance

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

(g) Retained Detailed Inspection of External Fuselage Skin, With 
Specific Delegation Approval Language

    This paragraph restates the requirements of paragraph (g) of AD 
2012-16-08, with specific delegation approval language. For all 
airplanes except airplanes that have incorporated auto-
pressurization modification HCM50259A during production: Within 12 
months after September 18, 2012 (the effective date of AD 2012-16-
08), do a detailed inspection to check for bulging, surface 
anomalies, and cracking of the fuselage skin adjacent to the 
discharge valve outlets (one frame fore and aft, one stringer above 
and below), in accordance with the Accomplishment Instructions of 
BAE Systems (Operations) Limited Inspection Service Bulletin ISB.21-
162, Revision 1, dated September 16, 2010. Repeat the inspection 
thereafter at intervals not to exceed 24 months.
    (1) If any bulging, surface anomalies, or cracking of the 
fuselage skin is found to be within the criteria defined in Subject 
53-00-00, ``Fuselage, General Description,'' of Chapter 53, 
``Fuselage,'' of the BAE SYSTEMS BAe 146 Series/AVRO 146-RJ Series 
Structural Repair Manual for Series 100-200, Revision 66, dated 
October 15, 2011 (for Model 146-100A and -200A, and Avro 146-RJ70A 
and 146-RJ85A airplanes); or Subject 53-00-00, ``Fuselage, General 
Description,'' of Chapter 53, ``Fuselage,'' of the BAe SYSTEMS BAE 
146 Series/AVRO 146-RJ Series Structural Repair Manual for Series 
300, Revision 44, dated October 15, 2011 (for Model 146-300A and 
Avro 146-RJ100A airplanes): Before further flight, repair the 
damage, in accordance with the Accomplishment Instructions specified 
in BAE Systems (Operations) Limited Inspection Service Bulletin 
ISB.21-162, Revision 1, dated September 16, 2010.
    (2) If any bulging, surface anomalies, or cracking of the 
fuselage skin is found exceeding the criteria specified by Subject 
53-00-00, ``Fuselage, General Description,'' of Chapter 53, 
``Fuselage,'' of the BAE SYSTEMS BAe 146 Series/AVRO 146-RJ Series 
Structural Repair Manual for Series 100-200, Revision 66, dated 
October 15, 2011 (for Model 146-100A and -200A, and Avro 146-RJ70A 
and 146-RJ85A airplanes); or Subject 53-00-00, ``Fuselage, General 
Description,'' of Chapter 53, ``Fuselage,'' of the BAE SYSTEMS BAE 
146 Series/AVRO 146-RJ Series Structural Repair Manual for Series 
300, Revision 44, dated October 15, 2011 (for Model 146-300A and 
Avro 146-RJ100A airplanes): Before further flight,

[[Page 72560]]

repair the condition according to 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).

(h) Retained Application of Sealant, With No Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2012-16-08, with no changes. For all airplanes except airplanes on 
which auto-pressurization modification HCM50259A was incorporated 
during production: Within 24 months after September 18, 2012 (the 
effective date of AD 2012-16-08), unless a repair has already been 
accomplished in accordance with paragraph (g) of this AD, apply 
additional PR1422A-2 or PR1764B-2 edge sealant between the water 
trap/air drier and the fuselage skin, in accordance with the 
Accomplishment Instructions of BAE Systems (Operations) Limited 
Inspection Service Bulletin ISB.21-162, Revision 1, dated September 
16, 2010. Application of additional sealant does not constitute 
terminating action for the repetitive detailed inspections required 
by paragraph (g) of this AD. Accomplishment of a repair as required 
by paragraph (g) of this AD terminates the repetitive inspection 
requirements of paragraph (g) of this AD.

(i) New Requirement of This AD: Inspection for Water Traps/Air Driers

    Within 12 months after the effective date of this AD, inspect 
the airplane to determine whether water traps/air driers are 
installed, in accordance with paragraph 2.C of BAE Systems 
(Operations) Limited Service Bulletin ISB.21-162, Revision 4, dated 
January 28, 2015 (``ISB.21-162 R4''). If there are no water traps/
air driers installed on an airplane, then no further inspections are 
required by this AD, except as required by paragraph (n) of this AD.

(j) New Requirement of This AD: Repetitive Inspections

    For airplanes that have water traps/air driers installed, 
determined as required by paragraph (i) of this AD: Within 12 months 
after the effective date of this AD, accomplish a detailed visual 
inspection for bulging, surface anomalies, and cracking of the 
external fuselage skin adjacent to the discharge valve outlets (one 
frame bay fore and aft, one stringer above and below), in accordance 
with the Accomplishment Instructions of paragraph 2.C. of ISB.21-162 
R4. Repeat the inspection of the external fuselage skin adjacent to 
the discharge valve outlets thereafter at intervals not to exceed 24 
months. Accomplishing an inspection required by this paragraph 
terminates the inspections required by paragraph (g) of this AD.

(k) New Requirement of This AD: Corrective Actions

    If, during any detailed visual inspection required by paragraph 
(j) of this AD, any bulging, surface anomalies, or cracking is 
found, before further flight, accomplish the applicable corrective 
action as specified in paragraphs (k)(1) and (k)(2) this AD.
    (1) If any bulging, surface anomalies, or cracking is found to 
be within the criteria as specified in the applicable service 
information specified in paragraph (k)(1)(i) or (k)(1)(ii) of this 
AD, before further flight, repair in accordance with the 
Accomplishment Instructions of paragraph 2.G. of ISB.21-162 R4.
    (i) For Model BAe 146-100A and -200A airplanes, and Model Avro 
146-RJ70A and 146-RJ85A airplanes: Subject 53-00-00, ``Fuselage, 
General Description,'' of Chapter 53, ``Fuselage,'' of the BAE 
SYSTEMS BAe 146 Series/AVRO 146-RJ Series Structural Repair Manual 
for Series 100-200, Revision 68, dated October 15, 2014.
    (ii) For Model BAe 146-300A airplanes and Model Avro 146-RJ100A 
airplanes: Subject 53-00-00, ``Fuselage, General Description,'' of 
Chapter 53, ``Fuselage,'' of the BAe SYSTEMS BAE 146 Series/AVRO 
146-RJ Series Structural Repair Manual for Series 300, Revision 46, 
dated October 15, 2014.
    (2) If any bulging, surface anomalies, or cracking is found 
exceeding the criteria as specified in the applicable service 
information specified in paragraph (k)(1)(i) or (k)(1)(ii) of this 
AD, before further flight, repair using a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or EASA; or BAE Systems (Operations) Limited's 
EASA DOA.

(l) New Requirement of This AD: Application of Sealant

    Within 24 months after the effective date of this AD, unless a 
repair has already been accomplished as required by paragraph (k) of 
this AD, apply additional sealant, in accordance with the 
Accomplishment Instructions of paragraph 2.C.(3) of ISB.21-162 R4. 
Application of additional sealant on an airplane does not constitute 
terminating action for the repetitive inspections required by 
paragraph (j) of this AD for that airplane.

(m) New Terminating Action for Inspections Required by Paragraph (j) of 
This AD

    Accomplishment of a repair on the forward (FWD) or aft (AFT) 
position as required by paragraph (k) of this AD constitutes 
terminating action for the repetitive inspections required by 
paragraph (j) of this AD for that FWD or AFT position.

(n) New Requirement of This AD: Actions for Airplanes on Which Water 
Trap/Air Driers Are Installed After the Effective Date of This AD

    For airplanes that, determined as required by paragraph (i) of 
this AD, do not have water traps/air driers installed: If water 
traps/air driers are installed in service after the effective date 
of this AD, accomplish the actions required by paragraphs (j), (k), 
and (l) of this AD on that airplane within the applicable compliance 
times specified in paragraphs (j), (k), and (l) of this AD; except 
that where paragraphs (j) and (l) of this AD refer to ``the 
effective date of this AD,'' this AD requires compliance within the 
specified compliance time after the installation of water traps/air 
driers.

(o) Credit for Previous Actions

    (1) This paragraph provides credit for inspections and sealant 
applications required by paragraphs (g) and (h) of this AD, if those 
actions were performed before September 18, 2012 (the effective date 
of AD 2012-16-08), using BAE SYSTEMS (OPERATIONS) LIMITED Inspection 
Service Bulletin ISB.21-162, dated June 7, 2010.
    (2) This paragraph provides credit for using criteria defined in 
the following subject of the applicable structural repair manual, as 
required by paragraphs (g)(1) and (g)(2) of this AD, if those 
criteria were used before September 18, 2012 (the effective date of 
AD 2012-16-08), using Subject 53-00-00, ``Fuselage, General--
Description,'' of Chapter 53, ``Fuselage,'' of the BAE SYSTEMS BAe 
146 Series/AVRO 146-RJ Series Structural Repair Manual for Series 
100-200, Revision 65, dated September 15, 2010 (for Model 146-100A 
and -200A, and Avro 146-RJ70A and 146-RJ85A airplanes); or Subject 
53-00-00, ``Fuselage, General--Description,'' of Chapter 53, 
``Fuselage,'' of the BAE SYSTEMS BAe 146 Series/AVRO 146-RJ Series 
Structural Repair Manual for Series 300, Revision 43, dated 
September 15, 2010 (for Model 146-300A and Avro 146-RJ100A 
airplanes).
    (3) This paragraph provides credit for actions required by 
paragraphs (i), (j), and (l) of this AD, if those actions were 
performed before the effective date of this AD using any of the 
service information specified in paragraphs (i)(3)(i) through 
(i)(3)(iv) of this AD.
    (i) BAE Systems (Operations) Limited Inspection Service Bulletin 
ISB.21-162, dated June 7, 2010.
    (ii) BAE Systems (Operations) Limited Inspection Service 
Bulletin ISB.21-162, Revision 1, dated September 16, 2010.
    (iii) BAE Systems (Operations) Limited Inspection Service 
Bulletin ISB.21-162, Revision 2, dated December 12, 2012.
    (iv) BAE Systems (Operations) Limited Inspection Service 
Bulletin ISB.21-162, Revision 3, dated January 15, 2013.

(p) 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: Theodore 
Thompson, Aerospace Engineer, telephone 425-227-1175; fax 425-227-
1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter must 
specifically reference this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement

[[Page 72561]]

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 European Aviation Safety Agency (EASA); or BAE Systems 
(Operations) Limited's EASA Design Organization Approval (DOA). If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0180, dated August 28, 
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-2016-9186.
    (2) 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 
RApublications@baesystems.com; Internet http://www.baesystems.com/Businesses/RegionalAircraft/index.htm. 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.

    Issued in Renton, Washington, on September 28, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-24201 Filed 10-19-16; 8:45 am]
 BILLING CODE 4910-13-P