81 FR 3350 - Airworthiness Directives; BAE Systems (Operations) Limited Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 13 (January 21, 2016)

Page Range		3350-3353
FR Document		2016-01088

We propose to supersede Airworthiness Directive (AD) 2012-11- 15, for all BAE Systems (Operations) Limited Model 4101 airplanes. AD 2012-11-15 currently requires a one-time detailed inspection for cracks, corrosion, and other defects of the rear face of the wing rear spar, and repair if necessary. Since we issued AD 2012-11-15, we received new reports of cracking found in the wing rear spar and technical analysis results confirmed that the crack initiation and propagation are due to fatigue, with no indication of any other crack initiation mechanism (e.g. stress corrosion). This proposed AD would require repetitive detailed inspections, and repair if necessary. We are proposing this AD to detect and correct cracking in the wing rear spar, which could propagate to a critical length, possibly affecting the structural integrity of the area and resulting in a fuel tank rupture, with consequent damage to the airplane and possible injury to its occupants.

Federal Register, Volume 81 Issue 13 (Thursday, January 21, 2016)

[Federal Register Volume 81, Number 13 (Thursday, January 21, 2016)]
[Proposed Rules]
[Pages 3350-3353]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-01088]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-0457; Directorate Identifier 2015-NM-084-AD]
RIN 2120-AA64


Airworthiness Directives; BAE Systems (Operations) Limited 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2012-11-
15, for all BAE Systems (Operations) Limited Model 4101 airplanes. AD 
2012-11-15 currently requires a one-time detailed inspection for 
cracks, corrosion, and other defects of the rear face of the wing rear 
spar, and repair if necessary. Since we issued AD 2012-11-15, we 
received new reports of cracking found in the wing rear spar and 
technical analysis results confirmed that the crack initiation and 
propagation are due to fatigue, with no indication of any other crack 
initiation mechanism (e.g. stress corrosion). This proposed AD would 
require repetitive detailed inspections, and repair if necessary. We 
are proposing this AD to detect and correct cracking in the wing rear 
spar, which could propagate to a critical length, possibly affecting 
the structural integrity of the area and resulting in a fuel tank 
rupture, with consequent damage to the airplane and possible injury to 
its occupants.

DATES: We must receive comments on this proposed AD by March 7, 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-

[[Page 3351]]

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.
    For service information identified in this proposed 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. 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-
0457; 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: 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: 

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-2016-0457; 
Directorate Identifier 2015-NM-084-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 March 31, 2012, we issued AD 2012-11-15, Amendment 39-17079 (77 
FR 36127, June 18, 2012). AD 2012-11-15 requires actions intended to 
address an unsafe condition on BAE Systems (Operations) Limited Model 
4101 airplanes.
    Since we issued AD 2012-11-15, Amendment 39-17079 (77 FR 36127, 
June 18, 2012), we received new reports of cracking found in the wing 
rear spar and technical analysis results confirmed that the crack 
initiation and propagation are due to fatigue, with no indication of 
any other crack initiation mechanism (e.g. stress corrosion).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0100, dated June 3, 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 4101 airplanes. The MCAI states:

    During an investigation of a fuel leak on the rear spar of a 
Jetstream 4100 aeroplane, 4 cracks were found between Ribs 6 and 7 
(immediately inboard of the inboard engine rib). The cracks 
initiated at adjacent fastener bores in the rear spar upper boom, 
and progressed downwards, diagonally, into the rear spar web.
    These cracks, if not detected and corrected, could propagate to 
a critical length, affecting the structural integrity of the area, 
possibly resulting in a fuel tank rupture with consequent damage to 
the aeroplane and injury to its occupants.
    Prompted by these findings, EASA issued [EASA] AD 2011-0096 
[which corresponds to FAA AD 2012-11-15, Amendment 39-17079 (77 FR 
36127, June 18, 2012)] to require a one-time [detailed] inspection 
[for cracks, corrosion, and other defects] of the rear face of the 
wing rear spar and the accomplishment of applicable corrective 
actions [i.e., repair], depending on findings. Initial analysis of 
the event did not lead to the conclusion that the cracking was 
fatigue related, therefore [EASA] AD 2011-0096 did not require 
repetitive inspections.
    Since that [EASA] AD [2011-0096] was issued, the results of the 
technical analysis confirmed that the cracks were due to fatigue, 
with no indication of any other crack initiation mechanism (e.g. 
stress corrosion). In addition, further similar in-service events 
have been reported. During investigation of those events, further 
metallurgical analysis indicated that the crack initiation and 
propagation are indeed fatigue driven and occur at the same 
location.
    To address this unsafe condition, a review of the inspection 
interval was undertaken based on the cracks from both aeroplanes and 
BAE Systems (Operations) Ltd issued Service Bulletin (SB) J41-A57-
029 Revision 3 in order to reduce the inspection interval of the 
wing rear spar from 2,000 flight cycles (FC) to 1,600 FC.
    For the reasons described above, this [EASA] AD supersedes AD 
2011-0096, without retaining its requirements, introduces repetitive 
inspections and, depending on findings, requires the accomplishments 
of applicable corrective action(s) [i.e., repair].

    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-
0457.

Related Service Information Under 1 CFR Part 51

    BAE Systems (Operations) Limited has issued Alert Service Bulletin 
J41-A57-029, Revision 3, dated April 8, 2014. The service information 
describes detailed inspections for cracks, corrosion, and other defects 
of the rear face of the wing rear spars.
    BAE Systems (Operations) Limited also has issued Subject 57-00-00, 
Wings General, of Chapter 57, Wings, of the Jetstream Series 4100 
Structural Repair Manual, Volume 1, Revision 32, dated October 15, 
2014. The service information describes procedures for doing certain 
wing repairs.
    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 develop on other products of the same 
type design.

Costs of Compliance

    We estimate that this proposed AD affects 15 airplanes of U.S. 
registry.
    We also estimate that it would take up to 25 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is

[[Page 3352]]

$85 per work-hour. Based on these figures, we estimate the cost of this 
proposed AD on U.S. operators to be up to $31,875, or up to $2,125 per 
product.
    We have received no definitive data that would enable us to provide 
a cost estimates for the on-condition actions (repairing cracks, 
corrosion, and defects) specified in this 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) 
2012-11-15, Amendment 39-17079 (77 FR 36127, June 18, 2012), and adding 
the following new AD:

BAE Systems (Operations) Limited: Docket No. FAA-2016-0457; 
Directorate Identifier 2015-NM-084-AD.

(a) Comments Due Date

    We must receive comments by March 7, 2016.

(b) Affected ADs

    This AD replaces AD 2012-11-15, Amendment 39-17079 (77 FR 36127, 
June 18, 2012).

(c) Applicability

    This AD applies to BAE (Operations) Limited Model 4101 
airplanes, certificated in any category, all models, and all serial 
numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by new reports of cracking found in the 
wing rear spar and technical analysis results confirmed that the 
crack initiation and propagation are due to fatigue, with no 
indication of any other crack initiation mechanism (e.g., stress 
corrosion). We are issuing this AD to detect and correct cracking in 
the wing rear spar, which could propagate to a critical length, 
possibly affecting the structural integrity of the area and 
resulting in a fuel tank rupture, with consequent damage to the 
airplane and possible injury to its occupants.

(f) Compliance

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

(g) Repetitive Inspections and Repair

    Within 30 days after the effective date of this AD, or within 
1,600 flight cycles since the most recent detailed inspection was 
done as specified in BAE Systems Alert Service Bulletin J41-A57-029, 
whichever occurs later: Do a detailed inspection for cracks, 
corrosion, and other defects (defects include scratches, dents, 
holes, damage to fastener holes, or damage to surface protection and 
finish) of the rear face of the wing rear spars, in accordance with 
the Accomplishment Instructions of BAE Systems Alert Service 
Bulletin J41-A57-029, Revision 3, dated April 8, 2014. Repeat the 
inspection thereafter at intervals not to exceed 1,600 flight 
cycles.
    (1) If any cracking, corrosion, or other defect is found within 
the criteria defined in Subject 57-00-00, Wings General, of Chapter 
57, Wings, of the Jetstream Series 4100 Structural Repair Manual, 
Volume 1, Revision 32, dated October 15, 2014: Before further 
flight, repair the affected area, in accordance with the repair 
instructions of Subject 57-00-00, Wings General, of Chapter 57, 
Wings, of the Jetstream Series 4100 Structural Repair Manual, Volume 
1, Revision 32, dated October 15, 2014.
    (2) If any cracking, corrosion, or other defect is found 
exceeding the criteria defined in Subject 57-00-00, Wings General, 
of Chapter 57, Wings, of the Jetstream Series 4100 Structural Repair 
Manual, Volume 1, Revision 32, dated October 15, 2014: 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).

(h) Repair Does Not Constitute Terminating Action Except for Certain 
Repairs

    Accomplishment of a repair as required by paragraphs (g)(1) and 
(g)(2) of this AD, does not constitute terminating action for the 
repetitive inspections required by paragraph (g) of this AD, unless 
the approved repair required by paragraph (g)(2) of this AD states 
otherwise (e.g., the approved repair states the repair terminates 
the inspections for the repaired area only).

(i) 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. The 
AMOC approval letter must specifically reference this AD.
    (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 European Aviation Safety Agency 
(EASA); or BAE Systems (Operations) Limited's EASA Design 
Organization Approval (DOA). If approved by the DOA,

[[Page 3353]]

the approval must include the DOA-authorized signature.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0100, dated June 3, 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-2016-0457.
    (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 
[email protected]; 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 January 13, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-01088 Filed 1-20-16; 8:45 am]
BILLING CODE 4910-13-P

3350 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Proposed Rules

proposed AD would not have a (d) Subject http://pubs.beechcraft.com. You may view
substantial direct effect on the States, on Air Transport Association (ATA) of this referenced service information at FAA,
the relationship between the national America Code 78, Exhaust. Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information
Government and the States, or on the (e) Unsafe Condition on the availability of this material at the
distribution of power and FAA, call 425–227–1221.
This AD was prompted by reports of
responsibilities among the various inadvertent stowage of the thrust reversers, Issued in Renton, Washington, on January
levels of government. which can result in high forward engine 8, 2016.
For the reasons discussed above, I thrust even though the throttle is Jeffrey E. Duven,
certify this proposed regulation: commanding reverse thrust. We are issuing
this AD to prevent inadvertent stowage of the Manager, Transport Airplane Directorate,
(1) Is not a ‘‘significant regulatory
thrust reversers, which could cause a runway Aircraft Certification Service.
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under overrun during a rejected takeoff or landing, [FR Doc. 2016–00951 Filed 1–20–16; 8:45 am]
and consequent structural failure and BILLING CODE 4910–13–P
the DOT Regulatory Policies and possible injury to occupants.
Procedures (44 FR 11034, February 26,
1979), (f) Compliance
DEPARTMENT OF TRANSPORTATION
(3) Will not affect intrastate aviation Comply with this AD within the
in Alaska, and compliance times specified, unless already
done.
Federal Aviation Administration
(4) Will not have a significant
economic impact, positive or negative, (g) Installation 14 CFR Part 39
on a substantial number of small entities Within 600 flight hours or 12 months after
under the criteria of the Regulatory [Docket No. FAA–2016–0457; Directorate
the effective date of this AD, whichever
Identifier 2015–NM–084–AD]
Flexibility Act. occurs first: Install kits having part numbers
140–9005 and 140–9006, in accordance with RIN 2120–AA64
List of Subjects in 14 CFR Part 39 the Accomplishment Instructions of
Air transportation, Aircraft, Aviation Beechcraft Mandatory Service Bulletin 78– Airworthiness Directives; BAE
safety, Incorporation by reference, 4133, dated May 2015, except as specified in Systems (Operations) Limited
paragraph (h) of this AD. Airplanes
Safety.
(h) Exception to Service Information
The Proposed Amendment AGENCY: Federal Aviation
A note in the Accomplishment Instructions Administration (FAA), DOT.
Accordingly, under the authority of Beechcraft Mandatory Service Bulletin 78–
ACTION: Notice of proposed rulemaking
delegated to me by the Administrator, 4133, dated May 2015, instructs operators to
the FAA proposes to amend 14 CFR part contact Beechcraft Corporation if any (NPRM).
39 as follows: difficulty is encountered in accomplishing
SUMMARY: We propose to supersede
the service bulletin. However, any deviation
from the actions required by paragraph (g) of Airworthiness Directive (AD) 2012–11–
PART 39—AIRWORTHINESS 15, for all BAE Systems (Operations)
DIRECTIVES this AD must be approved as an alternative
method of compliance (AMOC) under Limited Model 4101 airplanes. AD
■ 1. The authority citation for part 39 paragraph (i)(1) of this AD. 2012–11–15 currently requires a one-
continues to read as follows: (i) Alternative Methods of Compliance time detailed inspection for cracks,
(AMOCs) corrosion, and other defects of the rear
Authority: 49 U.S.C. 106(g), 40113, 44701. face of the wing rear spar, and repair if
(1) The Manager, Wichita Aircraft
§ 39.13 [Amended] Certification Office (ACO), FAA, has the necessary. Since we issued AD 2012–
authority to approve AMOCs for this AD, if 11–15, we received new reports of
■ 2. The FAA amends § 39.13 by adding
requested using the procedures found in 14 cracking found in the wing rear spar and
the following new airworthiness
CFR 39.19. In accordance with 14 CFR 39.19, technical analysis results confirmed that
directive (AD): send your request to your principal inspector the crack initiation and propagation are
Beechcraft Corporation (Type Certificate or local Flight Standards District Office, as due to fatigue, with no indication of any
Previously Held by Hawker Beechcraft appropriate. If sending information directly other crack initiation mechanism (e.g.
Corporation; Raytheon Aircraft to the manager of the ACO, send it to the stress corrosion). This proposed AD
Company): Docket No. FAA–2016–0460; attention of the person identified in
Directorate Identifier 2015–NM–078–AD. paragraph (j)(1) of this AD. would require repetitive detailed
(2) Before using any approved AMOC, inspections, and repair if necessary. We
(a) Comments Due Date notify your appropriate principal inspector, are proposing this AD to detect and
We must receive comments by March 7, or lacking a principal inspector, the manager correct cracking in the wing rear spar,
2016. of the local flight standards district office/ which could propagate to a critical
certificate holding district office. length, possibly affecting the structural
(b) Affected ADs
(j) Related Information integrity of the area and resulting in a
None.
(1) For more information about this AD,
fuel tank rupture, with consequent
(c) Applicability damage to the airplane and possible
contact Jeffrey Englert, Aerospace Engineer,
This AD applies to Beechcraft Corporation Mechanical Systems and Propulsion Branch, injury to its occupants.
(type certificate previously held by Hawker ACE–116W, FAA, Wichita Aircraft DATES: We must receive comments on
Beechcraft Corporation; Raytheon Aircraft Certification Office, 1801 Airport Road, this proposed AD by March 7, 2016.
jstallworth on DSK7TPTVN1PROD with PROPOSALS

Company) airplanes, certificated in any Room 100, Dwight D. Eisenhower National ADDRESSES: You may send comments by
category, as identified in paragraphs (c)(1) Airport, Wichita, KS 67209; phone: 316–946–
and (c)(2) of this AD. 4167; fax: 316–946–4107; email: any of the following methods:
(1) Model BAe.125 series 1000A and 1000B jeffrey.englert@faa.gov. • Federal eRulemaking Portal: Go to
airplanes, serial numbers 258151, 258159, (2) For service information identified in http://www.regulations.gov. Follow the
and 259004 through 259042 inclusive. this AD, contact Beechcraft Corporation, instructions for submitting comments.
(2) Model Hawker 1000 airplanes, serial TMDC, P.O. Box 85, Wichita, KS 67201– • Fax: 202–493–2251.
numbers 259003 and 259043 through 259052 0085; telephone 316–676–8238; fax 316–671– • Mail: U.S. Department of
inclusive. 2540; email tmdc@beechcraft.com; Internet Transportation, Docket Operations, M–

VerDate Sep<11>2014 15:09 Jan 20, 2016 Jkt 238001 PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 E:\FR\FM\21JAP1.SGM 21JAP1

Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Proposed Rules 3351

30, West Building Ground Floor, Room We will post all comments we propagation are indeed fatigue driven and
W12–140, 1200 New Jersey Avenue SE., receive, without change, to http:// occur at the same location.
Washington, DC 20590. www.regulations.gov, including any To address this unsafe condition, a review
• Hand Delivery: U.S. Department of personal information you provide. We of the inspection interval was undertaken
Transportation, Docket Operations, M– based on the cracks from both aeroplanes and
will also post a report summarizing each BAE Systems (Operations) Ltd issued Service
30, West Building Ground Floor, Room substantive verbal contact we receive Bulletin (SB) J41–A57–029 Revision 3 in
W12–140, 1200 New Jersey Avenue SE., about this proposed AD. order to reduce the inspection interval of the
Washington, DC, between 9 a.m. and 5 wing rear spar from 2,000 flight cycles (FC)
p.m., Monday through Friday, except Discussion
to 1,600 FC.
Federal holidays. On March 31, 2012, we issued AD For the reasons described above, this
For service information identified in 2012–11–15, Amendment 39–17079 (77 [EASA] AD supersedes AD 2011–0096,
this proposed AD, contact BAE Systems FR 36127, June 18, 2012). AD 2012–11– without retaining its requirements,
(Operations) Limited, Customer 15 requires actions intended to address introduces repetitive inspections and,
Information Department, Prestwick an unsafe condition on BAE Systems depending on findings, requires the
International Airport, Ayrshire, KA9 accomplishments of applicable corrective
(Operations) Limited Model 4101
action(s) [i.e., repair].
2RW, Scotland, United Kingdom; airplanes.
telephone +44 1292 675207; fax +44 Since we issued AD 2012–11–15, You may examine the MCAI in the
1292 675704; email RApublications@ Amendment 39–17079 (77 FR 36127, AD docket on the Internet at http://
baesystems.com; Internet http:// June 18, 2012), we received new reports www.regulations.gov by searching for
www.baesystems.com/Businesses/ of cracking found in the wing rear spar and locating Docket No. FAA–2016–
RegionalAircraft/index.htm. You may and technical analysis results confirmed 0457.
view this referenced service information that the crack initiation and propagation Related Service Information Under 1
at the FAA, Transport Airplane are due to fatigue, with no indication of CFR Part 51
Directorate, 1601 Lind Avenue SW., any other crack initiation mechanism
Renton, WA. For information on the (e.g. stress corrosion). BAE Systems (Operations) Limited
availability of this material at the FAA, The European Aviation Safety Agency has issued Alert Service Bulletin J41–
call 425–227–1221. (EASA), which is the Technical Agent A57–029, Revision 3, dated April 8,
for the Member States of the European 2014. The service information describes
Examining the AD Docket
Union, has issued EASA Airworthiness detailed inspections for cracks,
You may examine the AD docket on Directive 2015–0100, dated June 3, 2015 corrosion, and other defects of the rear
the Internet at http:// (referred to after this as the Mandatory face of the wing rear spars.
www.regulations.gov by searching for Continuing Airworthiness Information, BAE Systems (Operations) Limited
and locating Docket No. FAA–2016– or ‘‘the MCAI’’), to correct an unsafe also has issued Subject 57–00–00,
0457; or in person at the Docket condition for all BAE Systems Wings General, of Chapter 57, Wings, of
Management Facility between 9 a.m. (Operations) Limited Model 4101 the Jetstream Series 4100 Structural
and 5 p.m., Monday through Friday, airplanes. The MCAI states: Repair Manual, Volume 1, Revision 32,
except Federal holidays. The AD docket dated October 15, 2014. The service
contains this proposed AD, the During an investigation of a fuel leak on
the rear spar of a Jetstream 4100 aeroplane, information describes procedures for
regulatory evaluation, any comments 4 cracks were found between Ribs 6 and 7 doing certain wing repairs.
received, and other information. The (immediately inboard of the inboard engine This service information is reasonably
street address for the Docket Operations rib). The cracks initiated at adjacent fastener available because the interested parties
office (telephone 800–647–5527) is in bores in the rear spar upper boom, and have access to it through their normal
the ADDRESSES section. Comments will progressed downwards, diagonally, into the course of business or by the means
be available in the AD docket shortly rear spar web. identified in the ADDRESSES section.
after receipt. These cracks, if not detected and corrected,
FOR FURTHER INFORMATION CONTACT:
could propagate to a critical length, affecting FAA’s Determination and Requirements
the structural integrity of the area, possibly of This Proposed AD
Todd Thompson, Aerospace Engineer, resulting in a fuel tank rupture with
International Branch, ANM–116, consequent damage to the aeroplane and This product has been approved by
Transport Airplane Directorate, FAA, injury to its occupants. the aviation authority of another
1601 Lind Avenue SW., Renton, WA Prompted by these findings, EASA issued country, and is approved for operation
98057–3356; telephone 425–227–1175; [EASA] AD 2011–0096 [which corresponds in the United States. Pursuant to our
fax 425–227–1149. to FAA AD 2012–11–15, Amendment 39– bilateral agreement with the State of
SUPPLEMENTARY INFORMATION: 17079 (77 FR 36127, June 18, 2012)] to Design Authority, we have been notified
require a one-time [detailed] inspection [for of the unsafe condition described in the
Comments Invited cracks, corrosion, and other defects] of the
MCAI and service information
rear face of the wing rear spar and the
We invite you to send any written accomplishment of applicable corrective referenced above. We are proposing this
relevant data, views, or arguments about actions [i.e., repair], depending on findings. AD because we evaluated all pertinent
this proposed AD. Send your comments Initial analysis of the event did not lead to information and determined an unsafe
to an address listed under the the conclusion that the cracking was fatigue condition exists and is likely to exist or
ADDRESSES section. Include ‘‘Docket No. related, therefore [EASA] AD 2011–0096 did develop on other products of the same
FAA–2016–0457; Directorate Identifier not require repetitive inspections. type design.
jstallworth on DSK7TPTVN1PROD with PROPOSALS

2015–NM–084–AD’’ at the beginning of Since that [EASA] AD [2011–0096] was
your comments. We specifically invite issued, the results of the technical analysis Costs of Compliance
confirmed that the cracks were due to fatigue,
comments on the overall regulatory, We estimate that this proposed AD
with no indication of any other crack
economic, environmental, and energy initiation mechanism (e.g. stress corrosion). affects 15 airplanes of U.S. registry.
aspects of this proposed AD. We will In addition, further similar in-service events We also estimate that it would take up
consider all comments received by the have been reported. During investigation of to 25 work-hours per product to comply
closing date and may amend this those events, further metallurgical analysis with the basic requirements of this
proposed AD based on those comments. indicated that the crack initiation and proposed AD. The average labor rate is

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3352 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Proposed Rules

$85 per work-hour. Based on these the FAA proposes to amend 14 CFR part (1) If any cracking, corrosion, or other
figures, we estimate the cost of this 39 as follows: defect is found within the criteria defined in
proposed AD on U.S. operators to be up Subject 57–00–00, Wings General, of Chapter
PART 39—AIRWORTHINESS 57, Wings, of the Jetstream Series 4100
to $31,875, or up to $2,125 per product.
DIRECTIVES Structural Repair Manual, Volume 1,
We have received no definitive data Revision 32, dated October 15, 2014: Before
that would enable us to provide a cost further flight, repair the affected area, in
■ 1. The authority citation for part 39
estimates for the on-condition actions accordance with the repair instructions of
continues to read as follows:
(repairing cracks, corrosion, and defects) Subject 57–00–00, Wings General, of Chapter
specified in this AD. Authority: 49 U.S.C. 106(g), 40113, 44701. 57, Wings, of the Jetstream Series 4100
Structural Repair Manual, Volume 1,
Authority for This Rulemaking § 39.13 [Amended]
Revision 32, dated October 15, 2014.
Title 49 of the United States Code ■ 2. The FAA amends § 39.13 by (2) If any cracking, corrosion, or other
specifies the FAA’s authority to issue removing Airworthiness Directive (AD) defect is found exceeding the criteria defined
rules on aviation safety. Subtitle I, 2012–11–15, Amendment 39–17079 (77 in Subject 57–00–00, Wings General, of
FR 36127, June 18, 2012), and adding Chapter 57, Wings, of the Jetstream Series
section 106, describes the authority of
the following new AD: 4100 Structural Repair Manual, Volume 1,
the FAA Administrator. ‘‘Subtitle VII: Revision 32, dated October 15, 2014: Before
Aviation Programs,’’ describes in more BAE Systems (Operations) Limited: Docket further flight, repair using a method
detail the scope of the Agency’s No. FAA–2016–0457; Directorate approved by the Manager, International
authority. Identifier 2015–NM–084–AD. Branch, ANM–116, Transport Airplane
We are issuing this rulemaking under (a) Comments Due Date Directorate, FAA; or the European Aviation
the authority described in ‘‘Subtitle VII, We must receive comments by March 7, Safety Agency (EASA); or BAE Systems
Part A, Subpart III, Section 44701: 2016. (Operations) Limited’s EASA Design
General requirements.’’ Under that Organization Approval (DOA).
(b) Affected ADs
section, Congress charges the FAA with (h) Repair Does Not Constitute Terminating
promoting safe flight of civil aircraft in This AD replaces AD 2012–11–15, Action Except for Certain Repairs
air commerce by prescribing regulations Amendment 39–17079 (77 FR 36127, June
18, 2012). Accomplishment of a repair as required by
for practices, methods, and procedures paragraphs (g)(1) and (g)(2) of this AD, does
the Administrator finds necessary for (c) Applicability not constitute terminating action for the
safety in air commerce. This regulation This AD applies to BAE (Operations) repetitive inspections required by paragraph
is within the scope of that authority Limited Model 4101 airplanes, certificated in (g) of this AD, unless the approved repair
because it addresses an unsafe condition any category, all models, and all serial required by paragraph (g)(2) of this AD states
that is likely to exist or develop on numbers. otherwise (e.g., the approved repair states the
repair terminates the inspections for the
products identified in this rulemaking (d) Subject repaired area only).
action. Air Transport Association (ATA) of
America Code 57, Wings. (i) Other FAA AD Provisions
Regulatory Findings
The following provisions also apply to this
We determined that this proposed AD (e) Reason AD:
would not have federalism implications This AD was prompted by new reports of (1) Alternative Methods of Compliance
under Executive Order 13132. This cracking found in the wing rear spar and (AMOCs): The Manager, International
proposed AD would not have a technical analysis results confirmed that the Branch, ANM–116, Transport Airplane
crack initiation and propagation are due to Directorate, FAA, has the authority to
substantial direct effect on the States, on fatigue, with no indication of any other crack approve AMOCs for this AD, if requested
the relationship between the national initiation mechanism (e.g., stress corrosion). using the procedures found in 14 CFR 39.19.
Government and the States, or on the We are issuing this AD to detect and correct In accordance with 14 CFR 39.19, send your
distribution of power and cracking in the wing rear spar, which could request to your principal inspector or local
responsibilities among the various propagate to a critical length, possibly Flight Standards District Office, as
levels of government. affecting the structural integrity of the area appropriate. If sending information directly
For the reasons discussed above, I and resulting in a fuel tank rupture, with to the International Branch, send it to ATTN:
consequent damage to the airplane and Todd Thompson, Aerospace Engineer,
certify this proposed regulation: possible injury to its occupants.
1. Is not a ‘‘significant regulatory International Branch, ANM–116, Transport
action’’ under Executive Order 12866; (f) Compliance Airplane Directorate, FAA, 1601 Lind
2. Is not a ‘‘significant rule’’ under the Avenue SW., Renton, WA 98057–3356;
Comply with this AD within the
telephone 425–227–1175; fax 425–227–1149.
DOT Regulatory Policies and Procedures compliance times specified, unless already
done. Information may be emailed to: 9-ANM-116-
(44 FR 11034, February 26, 1979); AMOC-REQUESTS@faa.gov. Before using
3. Will not affect intrastate aviation in (g) Repetitive Inspections and Repair any approved AMOC, notify your appropriate
Alaska; and Within 30 days after the effective date of principal inspector, or lacking a principal
4. Will not have a significant this AD, or within 1,600 flight cycles since inspector, the manager of the local flight
economic impact, positive or negative, the most recent detailed inspection was done standards district office/certificate holding
on a substantial number of small entities as specified in BAE Systems Alert Service district office. The AMOC approval letter
under the criteria of the Regulatory Bulletin J41–A57–029, whichever occurs must specifically reference this AD.
Flexibility Act. later: Do a detailed inspection for cracks, (2) Contacting the Manufacturer: As of the
corrosion, and other defects (defects include effective date of this AD, for any requirement
jstallworth on DSK7TPTVN1PROD with PROPOSALS

List of Subjects in 14 CFR Part 39 scratches, dents, holes, damage to fastener in this AD to obtain corrective actions from
holes, or damage to surface protection and a manufacturer, the action must be
Air transportation, Aircraft, Aviation
finish) of the rear face of the wing rear spars, accomplished using a method approved by
safety, Incorporation by reference, in accordance with the Accomplishment the Manager, International Branch, ANM–
Safety. Instructions of BAE Systems Alert Service 116, Transport Airplane Directorate, FAA; or
The Proposed Amendment Bulletin J41–A57–029, Revision 3, dated the European Aviation Safety Agency
April 8, 2014. Repeat the inspection (EASA); or BAE Systems (Operations)
Accordingly, under the authority thereafter at intervals not to exceed 1,600 Limited’s EASA Design Organization
delegated to me by the Administrator, flight cycles. Approval (DOA). If approved by the DOA,

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Document Created: 2018-02-02 12:33:25
Document Modified: 2018-02-02 12:33:25

Category		Regulatory Information
Collection		Federal Register
sudoc Class		AE 2.7: GS 4.107: AE 2.106:
Publisher		Office of the Federal Register, National Archives and Records Administration
Section		Proposed Rules
Action		Notice of proposed rulemaking (NPRM).
Dates		We must receive comments on this proposed AD by March 7, 2016.
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.
FR Citation		81 FR 3350
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

81 FR 3350 - Airworthiness Directives; BAE Systems (Operations) Limited Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 81, Issue 13 (January 21, 2016)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration