Airworthiness Directives; BAE SYSTEMS (Operations) Limited Airplanes, 23208-23212 [2016-08957]
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Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules
(a) Comments Due Date
We must receive comments by June 6,
2016.
(b) Affected ADs
This AD replaces AD 2011–10–01,
Amendment 39–16682 (76 FR 25535, May 5,
2011). This AD affects AD 2014–16–23,
Amendment 39–17947 (79 FR 52545,
September 4, 2014).
(c) Applicability
This AD applies to Dassault Aviation
Model FALCON 7X airplanes, certificated in
any category, all serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 05, Time Limits/Maintenance
Checks.
(e) Reason
This AD was prompted by a revision of an
airworthiness limitations items (ALI)
document, which introduces new and more
restrictive maintenance requirements and
airworthiness limitations for airplane
structures and systems. We are issuing this
AD to prevent reduced structural integrity
and reduced control of these airplanes due to
the failure of system components.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Functional Test of the Ram Air
Turbine (RAT) Heater With New
Terminating Action and With Specific
Delegation Approval Language
This paragraph restates the requirements of
paragraph (g) of AD 2011–10–01,
Amendment 39–16682 (76 FR 25535, May 5,
2011), with new terminating action and with
specific delegation approval language. At the
applicable times specified in paragraph (g)(1)
or (g)(2) of this AD, do a functional test of
the RAT heater using a method approved by
either the Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA; or the European Aviation Safety
Agency (EASA); or Dassault Aviation’s EASA
Design Organization Approval (DOA). Repeat
the functional test of the RAT heater
thereafter at the applicable time specified in
paragraph (g)(1) or (g)(2) of this AD until the
revision required by paragraph (h) of this AD
is done. If any functional test fails, before
further flight, repair using a method
approved by either the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA; or
Dassault Aviation’s EASA DOA.
(1) For FALCON 7X airplanes on which
modification M0305 has not been done and
on which Dassault Service Bulletin 7X–018,
dated March 6, 2009, has not been done:
Within 650 flight hours after the effective
date of this AD, do a functional test of the
RAT heater and repeat the functional test of
the RAT heater thereafter at intervals not to
exceed 650 flight hours.
(2) For FALCON 7X airplanes on which
modification M0305 has been done or on
which Dassault Service Bulletin 7X–018,
dated March 6, 2009, has been done: Within
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1,900 flight hours after June 9, 2011 (the
effective date of AD 2011–10–01,
Amendment 39–16682 (76 FR 25535, May 5,
2011)) or after modification M0305 or
Dassault Service Bulletin 7X–018, dated
March 6, 2009, has been done, whichever
occurs later, do a functional test of the RAT
heater. Repeat the functional test of the RAT
heater thereafter at intervals not to exceed
1,900 flight hours.
Note 1 to paragraph (g) of this AD:
Additional guidance for doing the functional
test of the RAT heater required by paragraph
(g) of this AD can be found in Task 24–50–
25–720–801, Functional Test of the RAT
Heater, dated January 16, 2009, of the
Dassault FALCON 7X Aircraft Maintenance
Manual (AMM).
(h) New Requirement of This AD: Revise the
Maintenance or Inspection Program
Within 30 days after the effective date of
this AD, revise the maintenance or inspection
program, as applicable, by incorporating the
information specified in Chapter 5–40–00,
Airworthiness Limitations, DGT 107838,
Revision 4, dated February 2, 2015, of the
Dassault Falcon 7X Maintenance Manual
(MM). The initial compliance times for the
tasks specified in Chapter 5–40–00,
Airworthiness Limitations, DGT 107838,
Revision 4, dated February 2, 2015, of the
Dassault Falcon 7X MM are at the applicable
compliance times specified in Chapter 5–40–
00, Airworthiness Limitations, DGT 107838,
Revision 4, dated February 2, 2015, of the
Dassault Falcon 7X MM, or within 30 days
after the effective date of this AD, whichever
occurs later.
(i) Terminating Actions
(1) Accomplishment of the revision
required by paragraph (h) of this AD
terminates the requirements of paragraph (g)
of this AD.
(2) Accomplishment of the revision
required by paragraph (h) of this AD
terminates the requirements of paragraph (q)
of AD 2014–16–23, Amendment 39–17947
(79 FR 52545, September 4, 2014).
(j) No Alternative Actions, Intervals, and/or
Critical Design Configuration Control
Limitations (CDCCLs)
After the maintenance or inspection
program, as applicable, has been revised as
required by paragraph (h) of this AD, no
alternative actions (e.g., inspections),
intervals, and/or CDCCLs may be used unless
the actions, intervals, and/or CDCCLs are
approved as an alternative method of
compliance (AMOC) in accordance with the
procedures specified in paragraph (k)(1) of
this AD.
(k) 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
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Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Tom Rodriguez, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1137; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov.
(2) Contacting the Manufacturer: 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
EASA; or Dassault Aviation’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2015–0095, dated May 29, 2015, for related
information. You may examine the MCAI on
the Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2016–5464.
(2) For service information identified in
this AD, contact Dassault Falcon Jet
Corporation, Teterboro Airport, P.O. Box
2000, South Hackensack, NJ 07606;
telephone: 201–440–6700; Internet: https://
www.dassaultfalcon.com. 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 April 13,
2016.
Victor Wicklund,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–09005 Filed 4–19–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–5465; Directorate
Identifier 2015–NM–041–AD]
RIN 2120–AA64
Airworthiness Directives; BAE
SYSTEMS (Operations) Limited
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2010–10–
13, for all BAE SYSTEMS (Operations)
Limited Model BAe 146 and Avro 146
series airplanes. AD 2010–10–13
currently requires repetitive inspections
SUMMARY:
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Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules
of the wing fixed leading edge and front
spar structure for corrosion and
cracking, and repair if necessary. Since
we issued AD 2010–10–13, the Design
Approval Holder (DAH) has issued
revised inspection procedures that
eliminate a previously approved
inspection procedure. This proposed
AD would require revised inspection
procedures. We are proposing 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 wing.
DATES: We must receive comments on
this proposed AD by June 6, 2016.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://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.
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 https://
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.
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Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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 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
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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–2016–5465; Directorate Identifier
2015–NM–041–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 https://
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 April 30, 2010, we issued AD
2010–10–13, Amendment 39–16292 (75
FR 27419, May 17, 2010) (‘‘AD 2010–
10–13’’). AD 2010–10–13 requires
actions intended to address an unsafe
condition on all BAE SYSTEMS
(Operations) Limited Model BAe 146
and Avro 146 series airplanes.
Since we issued AD 2010–10–13, the
DAH has issued revised inspection
procedures that eliminates a previously
approved inspection procedure.
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, correction dated
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.
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To address this potential unsafe condition,
EASA issued AD 2009–0014 (https://
ad.easa.europa.eu/blob/easa_ad_2009_0014_
superseded.pdf/AD_2009–0014_1) [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:
• 12 years or 36,000 flight cycles,
whichever occurs earlier, for airplanes
on which the enhanced corrosion
protection has not been accomplished.
• 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 https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
5465.
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.
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Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules
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 these same
type designs.
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Costs of Compliance
We estimate that this proposed AD
affects 4 airplanes of U.S. registry.
The actions required by AD 2010–10–
13, and retained in this proposed 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
proposed 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 proposed 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
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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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 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:
■
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BAE SYSTEMS (Operations) Limited: Docket
No. FAA–2016–5465; Directorate
Identifier 2015–NM–041–AD.
(a) Comments Due Date
We must receive comments by June 6,
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
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 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 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 date of issuance of the
original airworthiness certificate or the date
of issuance of the original export certificate
of airworthiness, whichever occurs first.
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(iii) For airplanes with 15 years or more
since 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 raengliaison@
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baesystems.com, 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 inspection (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.
PO 00000
Frm 00024
Fmt 4702
Sfmt 4702
23211
(1) For airplanes with less than 9 years
since 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 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 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 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 date of issuance of the original
airworthiness certificate or the date of
issuance of the original export certificate of
airworthiness as of the 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 are 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
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.
E:\FR\FM\20APP1.SGM
20APP1
23212
Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules
Information may be emailed to: 9-ANM-116AMOC-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
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 DOAauthorized 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.
Lhorne on DSK5TPTVN1PROD with PROPOSALS
(o) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0047,
correction dated February 26, 2015, for
related information. This MCAI may be
found in the AD docket on the Internet at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2016–5465.
(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 https://
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 March
26, 2016.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2016–08957 Filed 4–19–16; 8:45 am]
BILLING CODE 4910–13–P
VerDate Sep<11>2014
14:51 Apr 19, 2016
Jkt 238001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–5595; Directorate
Identifier 2015–NM–087–AD]
RIN 2120–AA64
Airworthiness Directives; Zodiac Seats
California LLC Seating Systems
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Zodiac Seats California LLC seating
systems. This proposed AD was
prompted by a determination that the
affected seating systems may cause
serious injury to the occupant during
forward impacts when subjected to
certain inertia forces. This proposed AD
would require removing affected seating
systems. We are proposing this AD to
prevent serious injury to the occupant
during forward impacts in emergency
landing conditions.
DATES: We must receive comments on
this proposed AD by June 6, 2016.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
5595; 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 Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
PO 00000
Frm 00025
Fmt 4702
Sfmt 4702
FOR FURTHER INFORMATION CONTACT:
Patrick Farina, Aerospace Engineer,
Cabin Safety Branch, ANM–150L, FAA,
Los Angeles Aircraft Certification Office
(ACO), 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone:
562–627–5344; fax: 562–627–5210;
email: patrick.farina@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2016–5595; Directorate Identifier 2015–
NM–087–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 because of those
comments.
We will post all comments we
receive, without change, to https://
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
We determined that occupants of
certain Zodiac Seats California LLC
seating systems having model numbers
4157, 4170, and 4184, may experience
serious injury during forward impacts
when subjected to inertia forces as
defined by 14 CFR 25.561 and 14 CFR
25.562 (and thus are noncompliant with
14 CFR 25.785). The affected seating
systems are installed on, but not limited
to, various transport category airplanes.
The impact of the head onto a typical
transport passenger seat back during
seat qualification testing normally
results in an initial contact followed by
an unimpeded sliding motion down the
back of the seat. That type of interaction
does not typically result in excessive
neck loading or direct concentrated
loading on the neck. The design of the
affected seating systems introduce new
injury mechanisms such that the chin
can catch on the seat, causing high neck
bending loads and direct concentrated
loading on the neck. This interaction
between the head and the seat during
forward impacts can result in serious
injury to the occupant.
14 CFR 25.785 states that seat designs
cannot cause a serious injury to the
occupant when making proper use of
the seat and restraint and subjected to
the inertia forces specified in 14 CFR
E:\FR\FM\20APP1.SGM
20APP1
]]>Agencies
[Federal Register Volume 81, Number 76 (Wednesday, April 20, 2016)]
[Proposed Rules]
[Pages 23208-23212]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-08957]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-5465; Directorate Identifier 2015-NM-041-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) 2010-10-
13, for all BAE SYSTEMS (Operations) Limited Model BAe 146 and Avro 146
series airplanes. AD 2010-10-13 currently requires repetitive
inspections
[[Page 23209]]
of the wing fixed leading edge and front spar structure for corrosion
and cracking, and repair if necessary. Since we issued AD 2010-10-13,
the Design Approval Holder (DAH) has issued revised inspection
procedures that eliminate a previously approved inspection procedure.
This proposed AD would require revised inspection procedures. We are
proposing 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 wing.
DATES: We must receive comments on this proposed AD by June 6, 2016.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://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.
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 https://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 https://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 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-2016-5465;
Directorate Identifier 2015-NM-041-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 https://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 April 30, 2010, we issued AD 2010-10-13, Amendment 39-16292 (75
FR 27419, May 17, 2010) (``AD 2010-10-13''). AD 2010-10-13 requires
actions intended to address an unsafe condition on all BAE SYSTEMS
(Operations) Limited Model BAe 146 and Avro 146 series airplanes.
Since we issued AD 2010-10-13, the DAH has issued revised
inspection procedures that eliminates a previously approved inspection
procedure.
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, correction dated 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 (https://ad.easa.europa.eu/blob/easa_ad_2009_0014_superseded.pdf/AD_2009-0014_1) [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:
12 years or 36,000 flight cycles, whichever occurs
earlier, for airplanes on which the enhanced corrosion protection has
not been accomplished.
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 https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
5465.
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.
[[Page 23210]]
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 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 2010-10-13, and retained in this
proposed 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 proposed 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 proposed
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 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)
2010-10-13, Amendment 39-16292 (75 FR 27419, May 17, 2010), and adding
the following new AD:
BAE SYSTEMS (Operations) Limited: Docket No. FAA-2016-5465;
Directorate Identifier 2015-NM-041-AD.
(a) Comments Due Date
We must receive comments by June 6, 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 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 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 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
date of issuance of the original airworthiness certificate or the
date of issuance of the original export certificate of
airworthiness, whichever occurs first.
[[Page 23211]]
(iii) For airplanes with 15 years or more since 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
raengliaison@baesystems.com, 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 inspection (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 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 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 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
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 date of issuance
of the original airworthiness certificate or the date of issuance of
the original export certificate of airworthiness as of the 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 are 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
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.
[[Page 23212]]
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 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 2014-0047, correction dated
February 26, 2015, for related information. This MCAI may be found
in the AD docket on the Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2016-5465.
(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 https://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 March 26, 2016.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-08957 Filed 4-19-16; 8:45 am]
BILLING CODE 4910-13-P
