68690 Federal Register / Vol. 75, No. 216 / Tuesday, November 9, 2010 / Rules and Regulations 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. Send information to ATTN: Tak 

Kobayashi, Aerospace Engineer, Propulsion 

Branch, ANM–140S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6499; fax (425) 917–6590. 

Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

Material Incorporated by Reference 

(i) You must use Boeing Special Attention 

Service Bulletin 757–57–0070, dated January 

27, 2010, to do the actions required by this 

AD, unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/

code_of_federal_regulations/ibr_locations.

html. 

Issued in Renton, Washington, on October 

23, 2010. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–28160 Filed 11–8–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0548; Directorate 

Identifier 2010–NM–041–AD; Amendment 

39–16497; AD 2010–23–08] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model BD–700–1A10 and BD–700– 

1A11 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Following five reported cases of balance 

washer screw failure on similar RATs [ram 

air turbines]/air driven generators installed 

on other aircraft types, an investigation 

* * * determined that a specific batch of the 

screws had a metallographic non-conformity 

that increased their susceptibility to brittle 

fracture. * * * 

Failure of a balance washer screw can 

result in loss of the related balance washer, 

with consequent turbine imbalance. Such 

imbalance could potentially result in RAT 

structural failure (including blade failure), 

loss of RAT electrical power and structural 

damage to the aircraft and, if deployment was 

activated by a dual engine shutdown, could 

also result in loss of hydraulic power for the 

flight controls [and consequent reduced 

ability of the flightcrew to maintain the safe 

flight and landing of the airplane]. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

December 14, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 14, 2010. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Christopher Alfano, Aerospace 

Engineer, Airframe and Mechanical 

Systems Branch, ANE–171, FAA, New 

York Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7340; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on June 4, 2010 (75 FR 31731). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Following five reported cases of balance 

washer screw failure on similar RATs [ram 

air turbine]/air driven generators installed on 

other aircraft types, an investigation by 

Hamilton Sundstrand determined that a 

specific batch of the screws had a 

metallographic non-conformity that 

increased their susceptibility to brittle 

fracture. Subsequently, it was established 

that 187 RATs [Part Number (P/N) GL456– 

1101–7 and Hamilton Sundstrand P/Ns in the 

762826 series] had non-conforming screws 

installed either during production or possibly 

during maintenance or repair at Hamilton 

Sundstrand repair stations. 

Failure of a balance washer screw can 

result in loss of the related balance washer, 

with consequent turbine imbalance. Such 

imbalance could potentially result in RAT 

structural failure (including blade failure), 

loss of RAT electrical power and structural 

damage to the aircraft and, if deployment was 

activated by a dual engine shutdown, could 

also result in loss of hydraulic power for the 

flight controls [and consequent reduced 

ability of the flightcrew to maintain the safe 

flight and landing of the airplane]. 

This [Canadian] directive mandates 

checking of the RAT and replacing the 

balance washer screws, if required. It also 

prohibits future installation of unmodified 

RATs. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Actions Since NPRM Was Issued 

We have determined that this AD 

should refer to the latest service 

information. We have reviewed 

Bombardier Service Bulletin 700–1A11– 

24–014, Revision 02, dated March 15, 

2010; and Bombardier Service Bulletin 

700–24–075, Revision 02, dated March 

15, 2010; which introduce minor 

changes, but do not add any additional 

work. We have revised this final rule to 

include the latest version of the 

applicable Bombardier service 

information and to provide credit for 

work done before the effective date of 

this AD, in accordance with the 

previous revisions of the service 

information. 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
Federal Register / Vol. 75, No. 216 / Tuesday, November 9, 2010 / Rules and Regulations 68691 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

115 products of U.S. registry. We also 

estimate that it will take about 1 workhour per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $9,775, or $85 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM, 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 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 adding 

the following new AD: 

2010–23–08 Bombardier, Inc.: Amendment 

39–16497. Docket No. FAA–2010–0548; 

Directorate Identifier 2010–NM–041–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective December 14, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier, Inc. 

Model BD–700–1A10 and BD–700–1A11 

airplanes, serial numbers 9002 and 

subsequent; certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 24: Electrical power. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Following five reported cases of balance 

washer screw failure on similar RATs [ram 

air turbines]/air driven generators installed 

on other aircraft types, an investigation by 

Hamilton Sundstrand determined that a 

specific batch of the screws had a 

metallographic non-conformity that 

increased their susceptibility to brittle 

fracture. Subsequently, it was established 

that 187 RATs [Part Number (P/N) GL456– 

1101–7 and Hamilton Sundstrand P/Ns in the 

762826 series] had non-conforming screws 

installed either during production or possibly 

during maintenance or repair at Hamilton 

Sundstrand repair stations. 

Failure of a balance washer screw can 

result in loss of the related balance washer, 

with consequent turbine imbalance. Such 

imbalance could potentially result in RAT 

structural failure (including blade failure), 

loss of RAT electrical power and structural 

damage to the aircraft and, if deployment was 

activated by a dual engine shutdown, could 

also result in loss of hydraulic power for the 

flight controls [and consequent reduced 

ability of the flightcrew to maintain the safe 

flight and landing of the airplane]. 

This [Canadian] directive mandates 

checking of the RAT and replacing the 

balance washer screws, if required. It also 

prohibits future installation of unmodified 

RATs. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Inspection 

(g) For airplanes having serial numbers 

9002 through 9380 inclusive: At the earliest 

of the times identified in paragraphs (g)(1), 

(g)(2), (g)(3) and (g)(4) of this AD, inspect to 

determine the serial number of the installed 

ram air turbine (RAT), in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin listed in Table 1 

of this AD. This inspection may be 

conducted visually, which requires lowering 

the RAT. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the serial number of the RAT 

can be conclusively determined from that 

review. 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
68692 Federal Register / Vol. 75, No. 216 / Tuesday, November 9, 2010 / Rules and Regulations 

(1) Within 500 flight hours or 24 months 

after the effective date of this AD, whichever 

occurs first; or 

(2) Prior to the next in-flight or on-ground 

functional test of the RAT, whichever occurs 

first after the effective date of this AD; or 

(3) Prior to the next in-flight or on-ground 

operational test of the RAT, whichever 

occurs first after the effective date of this AD; 

or 

(4) Prior to the next scheduled RAT inflight deployment. 

(h) If the RAT serial number, as determined 

in paragraph (g) of this AD, is not listed in 

paragraph 1.A of the applicable service 

bulletin listed in Table 1 of this AD, no 

further action is required by this AD, except 

as required by paragraph (j) of this AD. 

TABLE 1—SERVICE BULLETINS

Model— Bombardier Service Bulletin— Revision— Dated— 

BD–700–1A11 ......................................................... 700–1A11–24–014 ................................................. 02 March 15, 2010. 

BD–700–1A10 ......................................................... 700–24–075 ........................................................... 02 March 15, 2010. 

(i) If the RAT serial number, determined in 

paragraph (g) of this AD, is listed in 

paragraph 1.A. of the applicable service 

bulletin listed in Table 1 of this AD, before 

further flight, inspect to determine if the 

symbol ‘‘24–7’’ is marked on the RAT 

identification plate, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin listed in Table 1 

of this AD. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the symbol ‘‘24–7’’ mark can be 

conclusively determined from that review. 

(1) If the symbol ‘‘24–7’’ is marked on the 

RAT identification plate, the balance washer 

screws have already been replaced and no 

further action is required by this AD, except 

as required by paragraph (j) of this AD. 

(2) If the symbol ‘‘24–7’’ is not marked on 

the RAT identification plate, before further 

flight, replace all balance washer screws with 

new balance washer screws, part number 

MS24667–14, and mark the RAT 

identification plate with the symbol ‘‘24–7,’’ 

in accordance with the Accomplishment 

Instructions of the applicable service bulletin 

listed in Table 1 of this AD. 

(j) For all airplanes: As of the effective date 

of this AD, no person may install on any 

airplane a replacement or spare RAT (P/N 

GL456–1101–7; Hamilton Sundstrand P/Ns 

in the 762826 series) having one of the S/Ns 

listed in paragraph 1.A. of the applicable 

service bulletin listed in Table 1 of this AD 

unless the balance washer screws have 

already been replaced and the symbol 

‘‘24–7’’ is marked on the RAT identification 

plate. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(k) Actions accomplished before the 

effective date of this AD, in accordance with 

the applicable service bulletin listed in 

Table 2 of this AD, are considered acceptable 

for compliance with the corresponding action 

specified in this AD. 

TABLE 2—CREDIT SERVICE BULLETINS

Model— Bombardier Service Bulletin— Revision— Dated— 

BD–700–1A11 ......................................................... 700–1A11–24–014 ................................................. 01 July 15, 2009. 

BD–700–1A10 ......................................................... 700–24–075 ........................................................... 01 July 15, 2009. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: 

Although Canadian Airworthiness Directive 

CF–2010–01, dated January 18, 2010, 

recommends accomplishing the visual 

inspection prior to the next scheduled inflight operational test of the RAT, we have 

determined that interval would not address 

the identified unsafe condition soon enough 

to ensure an adequate level of safety for the 

affected fleet in light of the degree of urgency 

associated with the subject unsafe condition. 

This difference has been coordinated with 

Transport Canada Civil Aviation (TCCA). 

Other FAA AD Provisions 

(l) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. Send information to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York, 

11590; telephone 516–228–7300; fax 516– 

794–5531. Before using any approved AMOC 

on any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(m) Refer to MCAI TCCA Airworthiness 

Directive CF–2010–01, dated January 18, 

2010; and Bombardier Service Bulletins 

700–24–075, Revision 02, dated March 15, 

2010, and 700–1A11–24–014, Revision 02, 

dated March 15, 2010; for related 

information. 

Material Incorporated by Reference 

(n) You must use Bombardier Service 

Bulletins 700–24–075, Revision 02, dated 

March 15, 2010; or Bombardier Service 

Bulletin 700–1A11–24–014, Revision 02, 

dated March 15, 2010; as applicable; to do 

the actions required by this AD, unless the 

AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 

514–855–7401; e-mail 

thd.crj@aero.bombardier.com; Internet http:// 

www.bombardier.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
Federal Register / Vol. 75, No. 216 / Tuesday, November 9, 2010 / Rules and Regulations 68693 

Issued in Renton, Washington on October 

21, 2010. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–28174 Filed 11–8–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1102; Directorate 

Identifier 2010–NM–016–AD; Amendment 

39–16507; AD 2010–23–18] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A380–800 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

During inspection in production and on inservice aircraft, a number of OverHeat 

Detection System (OHDS) installation nonconformities have been identified along the 

bleed air ducting. 

Some installation issues which may lead to 

a degraded leak detection capability have 

been reported. In case of hot air leakage, the 

potential degradation of the OHDS would not 

allow preventing damages to structure or 

components, and therefore could lead to an 

unsafe condition. 

* * * * * 

Nonconforming installation or a failure 

of the OHDS could allow undetected 

leakage of bleed air from the hot engine/ 

auxiliary power unit causing damage to 

the airplane structure and various 

airplane components and systems. This 

AD requires actions that are intended to 

address the unsafe condition described 

in the MCAI. 

DATES: This AD becomes effective 

November 24, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 24, 2010. 

We must receive comments on this 

AD by December 27, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–40, 1200 New Jersey 

Avenue, SE., Washington, DC, between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The 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, 

Aerospace Engineer, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, 1601 Lind Avenue, 

SW., Renton, Washington 98057–3356; 

telephone (425) 227–1175; fax (425) 

227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2009–0265, 

dated December 16, 2009 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

During inspection in production and on inservice aircraft, a number of OverHeat 

Detection System (OHDS) installation nonconformities have been identified along the 

bleed air ducting. 

Some installation issues which may lead to 

a degraded leak detection capability have 

been reported. In case of hot air leakage, the 

potential degradation of the OHDS would not 

allow preventing damages to structure or 

components, and therefore could lead to an 

unsafe condition. 

To ensure that in-service aeroplanes are 

free of such non-conformities, EASA AD 

2009–0066 required an inspection of the 

OHDS installation along the bleed air ducting 

and, in case of findings, to bring back the 

installation into the compliant configuration. 

That AD required a complete inspection for 

some MSN, and a partial inspection for MSN 

15, 20 and 22. This partial inspection has 

now been assessed to be insufficient to cover 

the unsafe condition. 

This [EASA] AD, which supersedes EASA 

AD 2009–0066, requires to perform: 

• An additional inspection on MSN 15, 20 

and 22 to render it complete, and 

• A complete inspection on additional 

MSN. 

Nonconforming installation or a failure 

of the OHDS could allow undetected 

leakage of bleed air from the hot engine/ 

auxiliary power unit causing damage to 

the airplane structure and various 

airplane components and systems. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A380–36–8009, including 

Service Bulletin Report Sheet, dated 

December 7, 2009. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of This 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 issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

There are no products of this type 

currently registered in the United States. 

However, this rule is necessary to 

ensure that the described unsafe 

condition is addressed if any of these 

products are placed on the U.S. Register 

in the future. 

Differences Between the AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1