Federal Register / Vol. 74, No. 138 / Tuesday, July 21, 2009 / Rules and Regulations 35777 

Issued in Renton, Washington, on July 2, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–16937 Filed 7–20–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1201; Directorate 

Identifier 2008–NM–007–AD; Amendment 

39–15922; AD 2009–11–12] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Airbus Model 

A310 series airplanes. That AD 

currently requires repetitive inspections 

of the fuselage skin to detect corrosion 

or fatigue cracking around and under 

the chafing plates of the wing root; 

repetitive inspections for fatigue 

cracking of frame 39, stringer 35; and 

corrective actions if necessary. The 

existing AD also provides for an 

optional terminating action for certain 

repetitive inspections, except for certain 

areas where corrosion was detected and 

reworked. This new AD reduces the 

intervals for accomplishing repetitive 

inspections in a certain area. This AD 

results from mandatory continuing 

airworthiness information originated by 

an aviation authority of another country 

to identify and correct an unsafe 

condition on an aviation product. We 

are issuing this AD to detect and correct 

fatigue cracks and corrosion around and 

under the chafing plates of the wing 

root, which could result in reduced 

structural integrity of the airplane. 

DATES: This AD becomes effective 

August 25, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of August 25, 2009. 

The Director of the Federal Register 

previously approved the incorporation 

by reference of Airbus Service Bulletin 

A310–53–2070, dated October 3, 1994, 

on June 3, 1998 (63 FR 23377, April 29, 

1998). 

ADDRESSES: For service information 

identified in this AD, contact Airbus 

SAS—EAW (Airworthiness Office), 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France; telephone +33 5 

61 93 36 96; fax +33 5 61 93 44 51; email: account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

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

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2004–14–06, amendment 

39–13715 (69 FR 41401, July 9, 2004). 

The existing AD applies to certain 

Airbus Model A310 series airplanes. 

That NPRM was published in the 

Federal Register on November 13, 2008 

(73 FR 67110). That NPRM proposed to 

continue to require repetitive 

inspections of the fuselage skin to detect 

corrosion or fatigue cracking around and 

under the chafing plates of the wing 

root; repetitive inspections for fatigue 

cracking of frame 39, stringer 35; and 

corrective actions if necessary. That 

NPRM also proposed to continue to 

provide for an optional terminating 

action for certain repetitive inspections, 

except for certain areas where corrosion 

was detected and reworked. In addition, 

that NPRM proposed to reduce the 

intervals for accomplishing the 

repetitive inspections in a certain area. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comment that has been 

received on the NPRM. FedEx supports 

the NPRM. 

Revisions to Paragraphs (f), (h), (i), and 

(j) of This AD 

We have revised paragraph (h) of this 

AD to give credit for actions done in 

accordance with Airbus Service Bulletin 

A310–53–2070, Revision 1, dated 

September 23, 1996. We also added 

Airbus Service Bulletin A310–53–2069, 

Revision 06, dated May 22, 2007, as an 

acceptable source of service information 

for compliance with the requirements of 

paragraphs (f) and (i) of this AD. We 

have also revised paragraph (j) of this 

AD to include a new Table 1 to specify 

the number, revision, and date of each 

service bulletin for which no reporting 

is required. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We also determined that these changes 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

Costs of Compliance 

This AD affects about 69 Model A310 

series airplanes of U.S. registry. The 

actions that are required by AD 2004– 

14–06 and retained in this AD take 

about 68 work hours per airplane, at an 

average labor rate of $80 per work hour. 

Based on these figures, the estimated 

cost of the currently required actions is 

$375,360, or $5,440 per airplane, per 

inspection cycle. 

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 have determined that this AD will 

not have federalism implications under 


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35778 Federal Register / Vol. 74, No. 138 / Tuesday, July 21, 2009 / Rules and Regulations 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

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. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–13715 (69 

FR 41401, July 9, 2004) and by adding 

the following new airworthiness 

directive (AD): 

2009–11–12 Airbus: Amendment 39–15922. 

Docket No. FAA–2008–1201; Directorate 

Identifier 2008–NM–007–AD. 

Effective Date 

(a) This AD becomes effective August 25, 

2009. 

Affected ADs 

(b) This AD supersedes AD 2004–14–06. 

Applicability 

(c) This AD applies to Airbus Model A310 

series airplanes, certificated in any category, 

on which Airbus Modifications 8888 and 

8889 have not been accomplished. 

Unsafe Condition 

(d) This AD results from mandatory 

continuing airworthiness information 

originated by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. We are 

issuing this AD to detect and correct fatigue 

cracks and corrosion around and under the 

chafing plates of the wing root, which could 

result in reduced structural integrity of the 

airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Requirements of AD 2004–14–06 

Repetitive Inspections and Corrective Actions 

(f) Except as provided by paragraphs (g), 

(k), and (l) of this AD: Within 4 years since 

date of manufacture, or within 12 months 

after June 3, 1998 (the effective date of AD 

98–09–20, amendment 39–10501), whichever 

occurs later, perform an inspection to detect 

discrepancies around and under the chafing 

plates of the wing root, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A310–53–2069, Revision 06, 

dated May 22, 2007; Revision 05, dated 

November 12, 2002; Revision 04, dated 

November 8, 2000; Revision 03, dated 

October 28, 1997; Revision 2, dated 

September 23, 1996; or Revision 1, dated 

September 19, 1995. If any discrepancy is 

found, prior to further flight, accomplish 

follow-on corrective actions (i.e., removal of 

corrosion, corrosion protection, high 

frequency eddy current inspection, x-ray 

inspection), as applicable, in accordance 

with the applicable service bulletin. Repeat 

the inspections thereafter at the intervals 

specified in the applicable service bulletin. 

After August 13, 2004 (the effective date of 

AD 2004–14–06), repeat the inspections 

thereafter at the intervals specified in Airbus 

Service Bulletin A310–53–2069, Revision 04, 

dated November 8, 2000; Airbus Service 

Bulletin A310–53–2069, Revision 05, dated 

November 12, 2002; or Airbus Service 

Bulletin A310–53–2069, Revision 06, dated 

May 22, 2007. 

(g) If any discrepancy is found during any 

inspection required by paragraph (f) of this 

AD, and Airbus Service Bulletin A310–53– 

2069, Revision 06, dated May 22, 2007; 

Revision 05, dated November 12, 2002; 

Revision 04, dated November 8, 2000; 

Revision 03, dated October 28, 1997; 

Revision 2, dated September 23, 1996; or 

Revision 1, dated September 19, 1995; as 

applicable; specifies to contact Airbus for 

appropriate action: Prior to further flight, 

repair in accordance with a method approved 

by the Manager, International Branch, ANM– 

116, FAA, Transport Airplane Directorate. 

Where differences in the compliance times or 

corrective actions exist between the service 

bulletin and this AD, the AD prevails. 

Optional Terminating Action 

(h) Except as provided by paragraph (i) of 

this AD: Accomplishment of the replacement 

of the stainless steel chafing plates with new 

chafing plates made of aluminum alloy, in 

accordance with Airbus Service Bulletin 

A310–53–2070, Revision 02, dated November 

8, 2000; or the original issue, dated October 

3, 1994; constitutes terminating action for the 

repetitive inspections required by paragraph 

(f) of this AD. Actions done in accordance 

with Airbus Service Bulletin A310–53–2070, 

Revision 1, dated September 23, 1996, are 

acceptable for compliance with actions 

required by this AD. 

Continuation of Repetitive Inspections 

(i) Except as provided by paragraphs (k) 

and (l) of this AD: Within 30 days after 

August 13, 2004, do a review of the airplane 

maintenance records to determine if any 

corrosion was detected and reworked on the 

left and/or right side of frame 39, stringer 35, 

during the accomplishment of any corrective 

action or repair specified in paragraphs (f) or 

(g) of this AD. If any corrective action or 

repair has been accomplished in this area, 

perform an inspection for fatigue cracking of 

frame 39, stringer 35, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–53–2069, Revision 06, 

dated May 22, 2007; Revision 05, dated 

November 12, 2002; or Revision 04, dated 

November 8, 2000. Do the initial inspection 

at the threshold specified in Figure 1 of the 

service bulletin, or within 30 days after 

August 13, 2004, whichever is later. Repeat 

the inspection thereafter at the intervals 

specified in Figure 1 of the service bulletin. 

If any discrepancy is found, prior to further 

flight, accomplish the applicable follow-on 

corrective actions, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–53–2069, Revision 06, 

dated May 22, 2007; Revision 05, dated 

November 12, 2002; or Revision 04, dated 

November 8, 2000. 

Submission of Information Not Required 

(j) Although the service bulletins specified 

in Table 1 of this AD specify to submit 

information to the manufacturer, this AD 

does not include such a requirement. 

TABLE 1—NO REPORTING REQUIREMENT FOR THESE SERVICE BULLETINS

Airbus Service Bulletin— Revision— Dated— 

A310–53–2069 ............................................................................................................................ 1 ................................ September 19, 1995. 

A310–53–2069 ............................................................................................................................ 2 ................................ September 23, 1996. 

A310–53–2069 ............................................................................................................................ 03 .............................. October 28, 1997. 

A310–53–2069 ............................................................................................................................ 04 .............................. November 8, 2000. 

A310–53–2069 ............................................................................................................................ 05 .............................. November 12, 2002. 


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Federal Register / Vol. 74, No. 138 / Tuesday, July 21, 2009 / Rules and Regulations 35779 

TABLE 1—NO REPORTING REQUIREMENT FOR THESE SERVICE BULLETINS—Continued 

Airbus Service Bulletin— Revision— Dated— 

A310–53–2069 ............................................................................................................................ 06 .............................. May 22, 2007. 

A310–53–2070 ............................................................................................................................ Original ...................... October 3, 1994. 

A310–53–2070 ............................................................................................................................ 1 ................................ September 23, 1996. 

A310–53–2070 ............................................................................................................................ 02 .............................. November 8, 2000. 

New Actions Required by This AD 

New Service Bulletin Revision 

(k) As of the effective date of this AD, use 

only the Accomplishment Instructions of 

Airbus Service Bulletin A310–53–2069, 

Revision 06, dated May 22, 2007, to do the 

inspections and corrective actions required 

by paragraphs (f) and (i) of this AD. 

Repetitive Inspections at Frame 39, Stringer 

35 at Reduced Intervals 

(l) As of the effective date of this AD, if any 

corrosion is found at frame 39, stringer 35, 

during any inspection required by this AD, 

do the repetitive inspections required by 

paragraphs (f) and (i) of this AD, as 

applicable, at the earlier of the times 

specified in paragraphs (l)(1) and (l)(2) of this 

AD. Repeat the inspections thereafter at 

intervals specified in Figure 1, Sheets 4 and 

5, of Airbus Service Bulletin A310–53–2069, 

Revision 06, dated May 22, 2007, except as 

provided by paragraph (m) of this AD. 

(1) At the next specified repeat interval 

specified in paragraph (f) of this AD. 

(2) At the later of the times specified in 

paragraphs (l)(2)(i) and (l)(2)(ii) of this AD, 

except as provided by paragraph (m) of this 

AD. 

(i) At the applicable threshold specified in 

Figure 1, Sheets 4 and 5, of Airbus Service 

Bulletin A310–53–2069, Revision 06, dated 

May 22, 2007. 

(ii) Within 900 flight cycles or 1,800 flight 

hours after the effective date of this AD, 

whichever occurs first. 

(m) Where Figure 1, Sheets 4 and 5, of 

Airbus Service Bulletin A310–53–2069, 

Revision 06, dated May 22, 2007, specifies to 

contact Airbus, do the inspections at 

threshold and repeat intervals approved by 

either the Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA; or the European Aviation Safety 

Agency (EASA) (or its delegated agent). 

Alternative Methods of Compliance (AMOCs) 

(n) 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. Send information to 

ATTN: Vladimir Ulyanov, Aerospace 

Engineer, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 1601 

Lind Avenue SW., Renton, Washington 

98057–3356; telephone (425) 227–1138; fax 

(425) 227–1149. Before using any approved 

AMOC on any airplane to which the AMOC 

applies, notify your appropriate principal 

inspector (PI) in the FAA Flight Standards 

District Office (FSDO), or lacking a PI, your 

local FSDO. 

Related Information 

(o) European Aviation Safety Agency 

(EASA) Airworthiness Directive 2007–0292, 

dated November 27, 2007, also addresses the 

subject of this AD. 

Material Incorporated by Reference 

(p) You must use Airbus Service Bulletin 

A310–53–2069, Revision 06, dated May 22, 

2007, as applicable, to do the actions 

required by this AD, unless the AD specifies 

otherwise. If you accomplish the optional 

terminating action specified in this AD, you 

must use the service bulletins specified in 

Table 2 of this AD, as applicable, unless the 

AD specifies otherwise. 

TABLE 2—MATERIAL INCORPORATED BY REFERENCE FOR OPTIONAL ACTIONS SPECIFIED IN THIS AD 

Airbus Service Bulletin— Revision— Dated— 

A310–53–2070 ............................................................................................................................ 02 .............................. November 8, 2000. 

A310–53–2070 ............................................................................................................................ Original ...................... October 3, 1994. 

Airbus Service Bulletin A310–53–2070, 

Revision 02, dated November 8, 2000, 

contains the following effective pages: 

Page No. Revision level shown on page Date shown on page 

1–13, 15–16, 21–22 ............................................................... 02 .......................................................................................... November 8, 2000. 

14, 17–18 ............................................................................... 1 ............................................................................................ September 23, 1996. 

19–20 ..................................................................................... Original .................................................................................. October 3, 1994. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information contained in Table 3 

of this AD under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

TABLE 3—NEW MATERIAL INCORPORATED BY REFERENCE

Airbus Service Bulletin— Revision— Dated— 

A310–53–2069 ............................................................................................................................ 06 .............................. May 22, 2007. 

A310–53–2070 ............................................................................................................................ 02 .............................. November 8, 2000. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of Airbus Service Bulletin A310– 

53–2070, dated October 3, 1994, on June 3, 

1998 (63 FR 23377, April 29, 1998). 

(3) For service information identified in 

this AD, contact Airbus SAS–EAW 

(Airworthiness Office), 1 Rond Point Maurice 


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35780 Federal Register / Vol. 74, No. 138 / Tuesday, July 21, 2009 / Rules and Regulations 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; e-mail: account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(4) 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 or 425–227–1152. 

(5) 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 July 2, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–17122 Filed 7–20–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0644; Directorate 

Identifier 2009–NM–059–AD; Amendment 

39–15972; AD 2009–15–09] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A380–841, –842, and –861 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 inspections in production and on 

in-service 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 * * *. 

* * * * * 

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 

August 5, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication, listed in the AD 

as of August 5, 2009. 

We must receive comments on this 

AD by August 20, 2009. 

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, 

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 2009–0066, 

dated March 19, 2009 (referred to after 

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

condition for the specified products. 

The MCAI states: 

During inspections in production and on 

in-service 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 aircraft are free of 

such non-conformities, this AD requires an 

inspection of the OHDS installation along the 

bleed air ducting and, in case of findings [any 

sensing element or insulation muff installed 

incorrectly], to bring back the installation 

into the compliant configuration. 

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. The 

inspection of the OHDS installation, for 

certain airplanes, consists of inspecting 

the APU overheat sensing elements APU 

1 Loop A and B, the APU overheat 

sensing elements APU 2 Loop A and B, 

the crossbleed overheat sensing 

element, the forward cargo compartment 

heating element, and the sensing 

element of the overheat detection unit of 

the wing. For certain other airplanes, 

inspecting the OHDS installation 

consists of inspecting the forward cargo 

compartment heating element. You may 

obtain further information by examining 

the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A380–36–8004, dated February 13, 

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 


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