Federal Register / Vol. 73, No. 198 / Friday, October 10, 2008 / Proposed Rules 60203 

Compliance 

(e) To address this problem, you must do 

the following, unless already done: 

Actions Compliance Procedures 

Install Stall Warning Heat Control Modification 

Kit, Piper part number 88452–002. 

Within the next 100 hours time-in-service after 

the effective date of this AD. 

As specified in Piper Mandatory Service Bulletin No. 1192, dated September 15, 2008, 

following Drawing No. 88452 dated June 

19, 2008. 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Atlanta 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: John 

Lee, Aerospace Engineer, Federal Aviation 

Administration, Atlanta ACO, One Crown 

Center, 1895 Phoenix Blvd., Suite 450, 

Atlanta, Georgia 30349; telephone: (770) 994– 

6736; fax: (770) 703–6097. 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 

(g) To get copies of the service information 

referenced in this AD, contact Piper Aircraft, 

Inc., 2926 Piper Drive, Vero Beach, Florida 

32960; telephone: (772) 567–4361; fax: (772) 

978–6573; Web site: http:// 

www.newpiper.com/. To view the AD docket, 

go to U.S. Department of Transportation, 

Docket Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 New 

Jersey Avenue, SE., Washington, DC 20590, 

or on the Internet at http:// 

www.regulations.gov. 

Issued in Kansas City, Missouri, on 

October 3, 2008. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E8–24136 Filed 10–9–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1082; Directorate 

Identifier 2007–NM–337–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 Airplanes; Model A300 B4–601, 

B4–603, B4–620, B4–622, B4–605R, 

B4–622R, F4–605R, F4–622R, and C4– 

605R Variant F Airplanes (Collectively 

Called A300–600 Series Airplanes); 

and Model A310 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to all of the 

airplanes identified above. The existing 

AD currently requires revising the FAAapproved maintenance program to 

include a new airplane maintenance 

manual task that specifies a detailed 

inspection after each ram air turbine 

(RAT) retraction. That existing AD also 

currently requires, for certain airplanes, 

a one-time inspection to detect breaks in 

the bottom flange fitting of the RAT and 

corrective actions, if necessary; for 

certain airplanes, an adjustment of the 

ejection jack; and, for certain other 

airplanes, replacement of the aluminum 

part with an improved steel part. This 

proposed AD also would continue to 

require certain actions for additional 

airplanes and would revise the FAAapproved maintenance program to 

include procedures for replacing the 

RAT swivel coupling fork fitting with a 

new steel part only. This proposed AD 

results from a report that an additional 

swivel coupling of the RAT yoke fitting 

was found cracked while accomplishing 

the requirements of the existing AD. We 

are proposing this AD to prevent 

misrigging of the ejection jack of the 

RAT and to ensure removal of any RAT 

yoke fitting made from aluminum 

material. Such conditions could result 

in a broken or cracked swivel coupling 

and consequent failure of the RAT yoke 

fitting, which could result in the loss of 

RAT function and possible loss of 

critical flight control systems in the 

event of certain emergency situations. 

DATES: We must receive comments on 

this proposed AD by November 10, 

2008. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this AD, contact Airbus, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France. 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket 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: 

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: 

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–2008–1082; Directorate Identifier 

2007–NM–337–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 http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 


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60204 Federal Register / Vol. 73, No. 198 / Friday, October 10, 2008 / Proposed Rules 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On January 24, 2007, we issued AD 

2007–03–09, amendment 39–14920 (72 

FR 5157, February 5, 2007), for all 

Airbus Model A300 airplanes; Model 

A300 B4–601, B4–603, B4–620, B4–622, 

B4–605R, B4–622R, F4–605R, F4–622R, 

and C4–605R variant F airplanes 

(collectively called A300–600 series 

airplanes); and Model A310 airplanes. 

That AD requires revising the FAAapproved maintenance program to 

include a new airplane maintenance 

manual task that specifies a detailed 

inspection after each ram air turbine 

(RAT) retraction. That AD also requires, 

for certain airplanes, a one-time 

inspection to detect breaks in the 

bottom flange fitting of the RAT and 

corrective actions, if necessary; for 

certain airplanes, an adjustment of the 

ejection jack; and, for certain other 

airplanes, replacement of the aluminum 

part with an improved steel part. That 

AD resulted from a report indicating 

that the swivel coupling of the RAT 

yoke fitting was found broken (due to a 

static overload as a result of the ejection 

jack of the RAT being misrigged). We 

issued that AD to prevent failure of the 

RAT yoke fitting, which could result in 

the loss of RAT function and possible 

loss of critical flight control systems in 

the event of certain emergency 

situations. 

Actions Since Existing AD Was Issued 

Since we issued AD 2007–03–09, 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, informed us that an 

additional swivel coupling of the RAT 

yoke fitting was found cracked while 

accomplishing the requirements of that 

AD. Investigation revealed that the crack 

was initiated by a stress-corrosion 

phenomenon on the aluminum material. 

Misrigging of the ejection jack of the 

RAT or a RAT yoke fitting that is made 

from aluminum material, if not 

corrected, could result in a broken or 

cracked swivel coupling and consequent 

failure of the RAT yoke fitting. This 

condition could result in the loss of 

RAT function and possible loss of 

critical flight control systems in the 

event of certain emergency situations. 

EASA has also informed us that 

certain Model A310 and A300–600 

series airplanes equipped with 

Hamilton Sundstrand RATs have a RAT 

yoke fitting made from aluminum 

material. Therefore, those airplanes are 

now subject to the same replacement 

requirements of AD 2007–03–09 as 

those airplanes equipped with Dowty 

Rotol RATs. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A310–57–2086, Revision 01, dated 

September 3, 2007 (for Model A310 

series airplanes); and Service Bulletin 

A300–57–6099, Revision 01, dated 

September 3, 2007 (for Model A300–600 

series airplanes). (AD 2007–03–09 refers 

to Airbus Service Bulletins A310–57– 

2086, dated March 1, 2005, and A300– 

57–6099, dated February 23, 2005; as 

applicable; as appropriate sources of 

service information for accomplishing 

the required replacement.) The 

replacement procedures specified in 

Revision 01 of the service bulletins are 

identical to that in the original issues of 

the service bulletins. No additional 

work is recommended for airplanes 

modified by the original issues of the 

service bulletins. 

Accomplishing the actions specified 

in the service information is intended to 

adequately address the unsafe 

condition. EASA mandated the service 

information and issued airworthiness 

directive 2007–0273, dated October 23, 

2007, to ensure the continued 

airworthiness of these airplanes in the 

European Union. 

FAA’s Determination and Requirements 

of the Proposed AD 

These airplanes are manufactured in 

France and are type certificated for 

operation in the United States under the 

provisions of section 21.29 of the 

Federal Aviation Regulations (14 CFR 

21.29) and the applicable bilateral 

airworthiness agreement. As described 

in FAA Order 8100.14A, ‘‘Interim 

Procedures for Working with the 

European Community on Airworthiness 

Certification and Continued 

Airworthiness,’’ dated August 12, 2005, 

EASA has kept the FAA informed of the 

situation described above. We have 

examined EASA’s findings, evaluated 

all pertinent information, and 

determined that AD action is necessary 

for airplanes of this type design that are 

certificated for operation in the United 

States. 

This proposed AD would supersede 

AD 2007–03–09. This proposed AD 

would continue to require replacing the 

aluminum yoke fitting of the swivel 

coupling of the RAT with a new steel 

yoke fitting and revising the FAAapproved maintenance program to 

include a new airplane maintenance 

manual task that specifies a detailed 

inspection after each RAT retraction. 

This proposed AD also would require 

those actions for additional airplanes 

and would revise the FAA-approved 

maintenance program to include 

procedures for replacing the RAT swivel 

coupling fork fitting with a new steel 

part only (the existing procedures allow 

replacement with either an aluminum or 

steel part). 

Difference Between This AD and EASA 

Airworthiness Directive 

EASA airworthiness directive 2007– 

0273 applies to the following U.S.- 

registered airplanes: Airbus Model A310 

and A300–600 series airplanes, except 

for airplanes on which Airbus 

Modification 12986 or 19578 has been 

done in production or on which Airbus 

Service Bulletin A310–57–2086 or 

A300–57–6099 has been done. This 

proposed AD, as did AD 2007–03–09, 

would affect all Model A300, A300–600, 

and A310 series airplanes. AD 2007–03– 

09 combined two French airworthiness 

directives (i.e., F–2005–089, dated June 

8, 2005, and F–2005–090 R1, dated July 

6, 2005), which affect additional 

airplanes not identified in EASA 

airworthiness directive 2007–0273. 

Unlike EASA airworthiness directive 

2007–0273, this proposed AD would 

require revising the FAA-approved 

maintenance program to specify an 

inspection for breaks of the bottom 

flange of the RAT swivel coupling yoke 

fitting after each RAT retraction; and 

replacement of the RAT swivel coupling 

yoke fitting with a new steel part. This 

action is necessary to ensure that only 

steel yoke fittings are installed. 

Change to Existing AD 

This proposed AD would retain 

certain requirements of AD 2007–03–09. 

Since AD 2007–03–09 was issued, the 

AD format has been revised, and certain 

paragraphs have been rearranged. As a 

result, the corresponding paragraph 

identifiers have changed in this 

proposed AD, as listed in the following 

table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in 

AD 2007–03–09 

Corresponding 

requirement in 

this 

proposed AD 

Paragraph (b) ...................... Paragraph (f). 

Paragraph (c) ...................... Paragraph (g). 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD. 


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Federal Register / Vol. 73, No. 198 / Friday, October 10, 2008 / Proposed Rules 60205 

ESTIMATED COSTS

Action Work hours Average labor 

rate per hour Parts Cost per airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Replacement ............................................ 14 $80 $470 $1,590 205 $325,950 

Revision of FAA-approved maintenance 

program ................................................ 1 80 None 80 205 16,400 

In consideration of the compliance 

time and effective date for 

accomplishing the replacement and 

revision of the FAA-approved 

maintenance program required by AD 

2007–03–09 (retained in paragraphs (f) 

and (g) of this proposed AD), we assume 

that operators of the affected airplanes 

have already initiated the required 

actions. The proposed AD would add no 

new costs associated with those 

airplanes. 

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 

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 that the 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); 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 proposed 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, 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 Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–14920 (72 

FR 5157, February 5, 2007) and adding 

the following new airworthiness 

directive (AD): 

Airbus: Docket No. FAA–2008–1082; 

Directorate Identifier 2007–NM–337–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by November 10, 2008. 

Affected ADs 

(b) This AD supersedes AD 2007–03–09. 

Applicability 

(c) This AD applies to all Model A300 

airplanes; Model A300 B4–601, B4–603, B4– 

620, B4–622, B4–605R, B4–622R, F4–605R, 

F4–622R, and C4–605R Variant F airplanes; 

and Model A310 airplanes, certificated in 

any category. 

Unsafe Condition 

(d) This AD results from a report that an 

additional swivel coupling of the RAT yoke 

fitting was found cracked while 

accomplishing the requirements of the 

existing AD. We are issuing this AD to 

prevent misrigging of the ejection jack of the 

ram air turbine (RAT) and to ensure removal 

of any RAT yoke fitting made from aluminum 

material. Such conditions could result in a 

broken or cracked swivel coupling and 

consequent failure of the RAT yoke fitting, 

which could result in the loss of RAT 

function and possible loss of critical flight 

control systems in the event of certain 

emergency situations. 

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. 

Certain Requirements of AD 2007–03–09: 

Replacement 

(f) For Model A300 airplanes, Model 

A300–600 series airplanes, and Model A310 

airplanes equipped with Dowty Rotol RATs, 

except airplanes on which Airbus 

Modification 12986 has been done: Within 12 

months after March 12, 2007 (the effective 

date of AD 2007–03–09), replace the RAT 

swivel coupling fork fitting with a new steel 

fitting, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–0244, dated March 

4, 2005 (for Model A300 airplanes); A300– 

57–6099, dated February 23, 2005 (for Model 

A300–600 series airplanes); or A310–57– 

2086, dated March 1, 2005 (for Model A310 

airplanes); as applicable; except as provided 

by paragraph (h) of this AD. 

Revisions of FAA-Approved Maintenance 

Program 

(g) For all airplanes: Within 3 months after 

March 12, 2007, incorporate the information 

in the applicable aircraft maintenance 

manual (AMM) specified in paragraphs (g)(1), 

(g)(2), and (g)(3) of this AD, into the FAAapproved maintenance program to specify an 

inspection for breaks of the bottom flange of 

the RAT swivel coupling yoke fitting after 

each RAT retraction; and replacement of the 

RAT swivel coupling yoke fitting with a new 

aluminum or steel part as applicable; in 

accordance with a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

Direction Ge ́ne ́rale de l’Aviation Civile (or its 

delegated agent); or European Aviation Safety 

Agency (or its delegated agent). The page 

blocks specified in paragraphs (g)(1), (g)(2), 

and (g)(3) of this AD, as applicable, are one 

approved method for the actions required by 

paragraph (g) of this AD. Thereafter, except 

as provided by paragraph (l) of this AD, no 

alternative inspection intervals may be 

approved for the bottom flange of the RAT 

swivel coupling yoke fitting. 

(1) Airbus A300–600 AMM, Chapter 29– 

25–00, Page Block 301, dated June 1, 2005. 

(2) Airbus A310 AMM, Chapter 29–25–00, 

Page Block 301, dated June 1, 2005. 


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(3) Airbus A300 AMM Chapter 29–25–00, 

Page Block 301, dated March 1, 2006. 

Note 1: After revising the maintenance 

program to include the required periodic 

inspections according to paragraph (g) or (k) 

of this AD, operators do not need to make a 

maintenance log entry to show compliance 

with this AD every time those inspections are 

accomplished thereafter. 

Note 2: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance according 

to paragraph (l) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued damage tolerance of the affected 

structure. The FAA has provided guidance 

for this determination in Advisory Circular 

(AC) 25–1529–1. 

New Requirements of This AD 

Revised Service Bulletins 

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

only the Accomplishment Instructions of 

Airbus Service Bulletin A310–57–2086, 

Revision 01, dated September 3, 2007 (for 

Model A310 series airplanes); or Airbus 

Service Bulletin A300–57–6099, Revision 01, 

dated September 3, 2007 (for Model A300– 

600 series airplanes); as applicable; to do the 

replacement required by paragraph (f) of this 

AD. 

Replacement 

(i) For airplanes identified in Table 1 of 

this AD: Before 102 months since first flight, 

or within 12 months after the effective date 

of this AD, whichever occurs later, replace 

the aluminum yoke fitting of the swivel 

coupling of the RAT with a new steel yoke 

fitting, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–57–2086, Revision 01, 

dated September 3, 2007 (for Model A310 

series airplanes); or Airbus Service Bulletin 

A300–57–6099, Revision 01, dated 

September 3, 2007 (for Model A300–600 

series airplanes); as applicable. 

TABLE 1—APPLICABILITY OF PARAGRAPH (I) OF THIS AD 

Model— Except for those airplanes on which— Or on which— 

(1) A310 series airplanes equipped with Hamilton Sundstrand RAT.Airbus Modification 12986 or 19578 has been 

done in production.

Airbus Service Bulletin A310–57–2086, dated 

March 1, 2005; or Revision 01, dated September 3, 2007 has been done in service. 

(2) A300–600 series airplanes equipped with 

Hamilton Sundstrand RAT.

Airbus Modification 12986 or 19578 has been 

done in production.

Airbus Service Bulletin A300–57–6099, dated 

February 23, 2005; or Revision 01, dated 

September 3, 2007; has been done in service. 

(j) Replacements done before the effective 

date of this AD in accordance with Airbus 

Service Bulletin A310–57–2086, dated March 

1, 2005 (for Model A310 series airplanes); or 

Airbus Service Bulletin A300–57–6099, 

dated February 23, 2005 (for Model A300– 

600 series airplane); as applicable; are 

acceptable for compliance with the 

requirements of paragraph (i) of this AD. 

Revision of FAA-Approved Maintenance 

Program 

(k) For all airplanes: Within 3 months after 

the effective date of this AD, incorporate the 

information in the applicable AMM specified 

in paragraphs (k)(1), (k)(2), and (k)(3) of this 

AD, into the FAA-approved maintenance 

program to specify an inspection for breaks 

of the bottom flange of the RAT swivel 

coupling yoke fitting after each RAT 

retraction; and replacement of the RAT 

swivel coupling yoke fitting with a new steel 

part; in accordance with a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

European Aviation Safety Agency (or its 

delegated agent). The page blocks specified 

in paragraphs (k)(1), (k)(2), and (k)(3) of this 

AD, as applicable, that contain the inspection 

and replacement described previously are 

one approved method for the actions 

required by paragraph (k) of this AD. 

Thereafter, except as provided by paragraph 

(l) of this AD, no alternative inspection 

intervals may be approved for the bottom 

flange of the RAT swivel coupling yoke 

fitting. Accomplishing this incorporation 

terminates the requirements of paragraph (g) 

of this AD. 

(1) Airbus A300–600 AMM, Chapter 29– 

25–00, Page Block 301. 

(2) Airbus A310 AMM, Chapter 29–25–00, 

Page Block 301. 

(3) Airbus A300 AMM Chapter 29–25–00, 

Page Block 301. 

Alternative Methods of Compliance 

(AMOCs) 

(l) The Manager, International Branch, 

ANM–116, 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 

(m) European Aviation Safety Agency 

(EASA) airworthiness directive 2007–0273, 

dated October 23, 2007, and French 

airworthiness directive F–2005–089, dated 

June 8, 2005, also address the subject of this 

AD. 

Issued in Renton, Washington, on October 

2, 2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–24151 Filed 10–9–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1083; Directorate 

Identifier 2008–NM–130–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model DHC–8–400 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

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: 

There have been several cases reported 

where the landing gear did not retract after 

take-off. Subsequent investigation revealed 

this was caused by fatigue failure of the nose 

landing gear electrical harness. In 

conjunction with one engine being 

inoperable, this could, in certain operating 

conditions, affect continued safe flight and 

landing. 


sroberts on PROD1PC70 with PROPOSALS