Federal Register / Vol. 74, No. 129 / Wednesday, July 8, 2009 / Rules and Regulations 32423 

AD to prevent uncontained failure of the HPC 

12th stage disk and airplane damage. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed at the 

following compliance times: 

(1) For PW2040 turbofan engines, within 

200 cycles-in-service (CIS) after the effective 

date of this AD, unless the actions have 

already been done. 

(2) For PW2037 and PW2037(M) turbofan 

engines, within 400 CIS after the effective 

date of this AD, unless the actions have 

already been done. 

Non-Destructive Inspection 

(f) Have a special eddy-current inspection 

performed on the 12th stage disks installed 

in the HPC drum rotor disk assemblies listed 

in Table 1 of this AD, for cracks. Use 

paragraph 1 of the Accomplishment 

Instructions of Pratt & Whitney Alert Service 

Bulletin No. PW2000 A72–736, dated January 

5, 2009, to do the special eddy current 

inspection. 

Alternative Methods of Compliance 

(g) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Related Information 

(h) Contact Mark Riley, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: mark.riley@faa.gov; telephone 

(781) 238–7758, fax (781) 238–7199. 

Material Incorporated by Reference 

(i) You must use Pratt & Whitney Alert 

Service Bulletin No. PW2000 A72–736, dated 

January 5, 2009, to have the special eddy 

current inspections performed by this AD. 

The Director of the Federal Register approved 

the incorporation by reference of this service 

bulletin in accordance with 5 U.S.C. 552(a) 

and 1 CFR part 51. Contact Pratt & Whitney, 

400 Main Street, East Hartford, CT 06108, for 

a copy of this service information. You may 

review copies at the FAA, New England 

Region, 12 New England Executive Park, 

Burlington, MA; or 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/

cfr/ibr-locations.html. 

Issued in Burlington, Massachusetts, on 

June 23, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–15398 Filed 7–7–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1116; Directorate 

Identifier 2007–NM–231–AD; Amendment 

39–15954; AD 2009–14–04] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–100, –200, –200C, –300, 

–400, and –500 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes. 

For certain airplanes, this AD requires 

deactivating or modifying the wiring to 

the outboard landing lights, until the 

wire bundles and electrical connectors 

have been replaced. For all airplanes, 

this AD also requires inspecting for any 

broken, damaged, or missing fairleads, 

grommets, and wires in the four 

electrical junction boxes of the main 

wheel well, and corrective actions if 

necessary. For certain airplanes, this AD 

also requires replacing certain wire 

bundles for the landing lights and fuel 

shutoff valves, and related investigative, 

other specified, and corrective actions if 

necessary. For certain airplanes, this AD 

also requires replacing of certain 

electrical connectors and backshell 

clamps. This AD results from reports of 

uncommanded engine shutdowns and 

burned and damaged wire bundles 

associated with the outboard landing 

lights and engine fuel shutoff valves. 

This AD also results from reports of 

damaged and missing grommets and 

broken and damaged fairleads in the 

electrical junction boxes of the main 

wheel well. We are issuing this AD to 

prevent a hot short between the 

outboard landing light and fuel shutoff 

valve circuits, which could result in an 

uncommanded engine shutdown. We 

are also issuing this AD to prevent 

corrosion of the electrical connectors of 

the wing rear spars, which could result 

in short circuits and consequent 

incorrect functioning of airplane 

systems needed for safe flight and 

landing. 

DATES: This AD is effective August 12, 

2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of August 12, 2009. 

ADDRESSES: 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. 

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: 

Stephen Oshiro, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6480; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to 

certain Boeing Model 737–100, –200, 

–200C, –300, –400, and –500 series 

airplanes. That NPRM was published in 

the Federal Register on October 22, 

2008 (73 FR 62937). That NPRM 

proposed to require deactivating or 

modifying of the wiring to the outboard 

landing lights, until the wire bundles 

and electrical connectors have been 

replaced. For all airplanes, that NPRM 

proposed to require inspecting for any 

broken, damaged, or missing fairleads, 

grommets, and wires in the four 

electrical junction boxes of the main 

wheel well, and corrective actions if 

necessary. For certain airplanes, that 

NPRM also proposed to require 

replacing of certain wire bundles for the 

landing lights and fuel shutoff valves, 

and related investigative, other 

specified, and corrective actions if 

necessary. For certain airplanes, that 

NPRM also proposed to require 

replacing certain electrical connectors 

and backshell clamps. 


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32424 Federal Register / Vol. 74, No. 129 / Wednesday, July 8, 2009 / Rules and Regulations 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received from 

the two commenters. 

Support for the NPRM 

Boeing concurs with the contents of 

the NPRM. 

Request for Work Instructions 

Correction 

Southwest Airlines states that there 

appears to be an error in the work 

instructions of Boeing Alert Service 

Bulletin 737–33A1140, dated May 22, 

2006. Figure 2 (left wing) gives 

instructions to route new wires, and 

Figure 4 (right wing) has no work 

instructions for wire termination in 

either figure. 

We infer that Southwest Airlines 

requests that we revise the final rule to 

account for these apparent service 

bulletin errors and that clarification is 

necessary. Instructions for terminating 

the new wires are provided by the work 

instructions associated with Figure 1 

(left wing) and Figure 3 (right wing) in 

Boeing Alert Service Bulletin 737– 

33A1140, dated May 22, 2006. We have 

not changed the final rule regarding this 

issue. 

Request Alternative to Corrective 

Action 

Southwest Airlines proposes that we 

revise the NPRM to require the use of 

detailed inspections of the referenced 

wire bundles of the landing lights and 

fuel shutoff valves, as well as 

performing operational checks of these 

items at 180-day intervals from the 

effective date of this AD, as a substitute 

for the corrective actions described by 

paragraph (f) of the proposed AD. The 

commenter states that the deactivation 

of the outboard landing lights per 

paragraph (f)(1) of the NPRM would be 

considered a temporary solution and 

would not provide a positive 

operational situation. 

We disagree. The alternative 

corrective action proposed by the 

commenter will not effectively address 

the potential unsafe condition for the 

following reasons: 

1. The short circuiting of the wires for 

the landing lights and engine fuel 

shutoff valves occurs within the wire 

bundle, which is covered by a protective 

overbraid. It is not possible to visually 

inspect the affected wires without 

partially removing the overbraid and 

disturbing the wires, which could cause 

the wires to be damaged. 

2. Operational testing of the outboard 

landing lights and the engine fuel 

shutoff valves at 180-day intervals will 

not be effective in detecting the failures 

since the short circuits occur suddenly 

and are not preceded by symptoms that 

indicate the onset of the failure. 

3. The corrective actions described by 

paragraph (f) of this AD are intended to 

be a temporary solution to the potential 

unsafe condition until sufficient 

replacement wire bundles can be 

manufactured to allow incorporating the 

final corrective action into the affected 

airplanes. The final corrective action is 

described by paragraph (g) of this AD. 

The compliance time for doing the final 

corrective action required by paragraph 

(g) of this AD is within 60 months. 

Mandating the final corrective action 

without the corrective action of 

paragraph (f) is not considered 

acceptable because this would expose 

the airplanes of the affected fleet to the 

potential unsafe condition for an 

excessive amount of time. 

We have not changed the final rule 

regarding this issue. However, operators 

may request approval of an alternative 

method of compliance in accordance 

with paragraph (j) of this AD. 

Explanation of Changes to Costs of 

Compliance 

We have revised the Costs of 

Compliance to specify only the per 

product cost for deactivating and 

modifying the wiring to the outboard 

landing lights. We are not specifying the 

total cost for all affected airplanes for 

those two actions because operators may 

accomplish either action. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that the actions specified 

in Boeing Alert Service Bulletin 737– 

33A1140 affect about 511 Model 737– 

300, –400, and –500 series airplanes of 

U.S. registry. Operators may accomplish 

either the deactivation or modification. 

We estimate that it takes about 1 

work-hour per product to comply with 

the deactivation specified in this AD. 

The average labor rate is $80 per workhour. Based on these figures, we 

estimate the cost of the deactivation, if 

done, to the U.S. operators to be $80 per 

product. 

We estimate that it takes about 31 

work-hours per product to comply with 

the modification specified in this AD. 

The average labor rate is $80 per workhour. Required parts for the 

modification cost about $573 per 

product. Based on these figures, we 

estimate the cost of modification, if 

done, to the U.S. operators to be $3,053 

per product. 

We estimate that the actions specified 

in Boeing Service Bulletin 737–28– 

1241, Revision 1, dated August 31, 

2007, affect up to 891 Model 737–100, 

–200, –200C, –300, –400, and –500 

series airplanes of U.S. registry. The 

following table provides the estimated 

costs, at an average labor rate of $80 per 

work-hour, for U.S. operators to comply 

with the actions specified in that service 

bulletin. 

ESTIMATED COSTS

Action Work-hours Parts Cost per 

airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Part 1—Replacement of wire bundles ................ Up to 91 ................. Up to $18,439 ........ $25,719 511 $13,142,409 

Part 2—Inspection of junction boxes .................. 1 ............................. 0 ............................. 80 891 71,280 

Part 3—Replacement of electrical connectors ... 2 ............................. 298 ......................... 458 400 183,200 

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 


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Federal Register / Vol. 74, No. 129 / Wednesday, July 8, 2009 / Rules and Regulations 32425 

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 

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 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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

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: 

2009–14–04 Boeing: Amendment 39–15954. 

Docket No. FAA–2008–1116; Directorate 

Identifier 2007–NM–231–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective August 12, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 737– 

100, –200, –200C, –300, –400, and –500 

series airplanes, certificated in any category; 

as identified in Boeing Service Bulletin 737– 

28–1241, Revision 1, dated August 31, 2007. 

Unsafe Condition 

(d) This AD results from reports of 

uncommanded engine shutdowns and 

burned and damaged wire bundles associated 

with the outboard landing lights and engine 

fuel shutoff valves. This AD also results from 

reports of damaged and missing grommets 

and broken and damaged fairleads in the 

electrical junction boxes of the main wheel 

well. We are issuing this AD to prevent a hot 

short between the outboard landing light and 

fuel shutoff valve circuits, which could result 

in an uncommanded engine shutdown. We 

are also issuing this AD to prevent corrosion 

of the electrical connectors of the wing rear 

spars, which could result in short circuits 

and consequent incorrect functioning of 

airplane systems needed for safe flight and 

landing. 

Compliance 

(e) Comply with this AD within the 

compliance times specified, unless already 

done. 

Deactivating or Modifying the Outboard 

Landing Lights 

(f) For Model 737–300, –400, and –500 

series airplanes identified in Boeing Alert 

Service Bulletin 737–33A1140, dated May 

22, 2006: Within 180 days after the effective 

date of this AD, accomplish the actions 

specified in either paragraph (f)(1) or (f)(2) of 

this AD. Accomplishing the applicable 

actions required by paragraph (g) of this AD 

terminates the requirements of this 

paragraph. 

(1) Deactivate the outboard landing lights 

by accomplishing all of the actions specified 

in Part 1 of the Accomplishment Instructions 

of Boeing Alert Service Bulletin 737– 

33A1140, dated May 22, 2006. 

Note 1: The Master Minimum Equipment 

List (MMEL) prohibits dispatching an 

airplane for night operations with 

deactivated outboard landing lights in the 

event that either of the inboard landing lights 

fail. Operators should note that, if the 

outboard landing lights are deactivated in 

accordance with Part 1 of Boeing Alert 

Service Bulletin 737–33A1140, dated May 

22, 2006, there is no MMEL relief allowing 

for this configuration for night operations 

should any inboard landing light fail. 

(2) Modify the wiring to the outboard 

landing lights by accomplishing all of the 

actions specified in Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–33A1140, dated May 

22, 2006. 

Inspection and Replacements 

(g) For all airplanes: Within 60 months 

after the effective date of this AD, do the 

applicable actions specified in paragraphs 

(g)(1), (g)(2), and (g)(3) of this AD, by 

accomplishing all of the applicable actions 

specified in the Accomplishment 

Instructions of Boeing Service Bulletin 737– 

28–1241, Revision 1, dated August 31, 2007. 

For Model 737–300, –400, and –500 series 

airplanes identified in Boeing Alert Service 

Bulletin 737–33A1140, dated May 22, 2006, 

accomplishing the applicable actions 

required by this paragraph terminates the 

requirements of paragraph (f) of this AD. 

(1) Replace the wire bundles for the 

landing lights and fuel shutoff valves with 

new, redesigned wire bundles, and do the 

related investigative, other specified, and 

corrective actions, as applicable. The related 

investigative, other specified, and corrective 

actions must be done before further flight 

after the replacement. 

(2) Do a detailed inspection for any broken, 

damaged, or missing fairleads, any damaged 

or missing grommets, and any chafed or 

damaged wires or wire bundles in the four 

electrical junction boxes of the main wheel 

well, and do the applicable corrective 

actions. The corrective actions must be done 

before further flight after the inspection. 

(3) Replace the electrical connectors and 

backshell clamps with new, improved 

electrical connectors and backshell clamps, 

as applicable. 

Credit for Actions Done According to 

Previous Issue of Service Bulletin 

(h) For airplanes identified as Groups 1 

and 2 in Boeing Service Bulletin 737–28– 

1241, Revision 1, dated August 31, 2007: 

Actions done before the effective date of this 

AD in accordance with Boeing Service 

Bulletin 737–28–1241, dated April 7, 2006, 

are acceptable for compliance with the 

requirements of paragraph (g) of this AD. 

(i) For all airplanes: Actions done before 

the effective date of this AD in accordance 

with Part 2 of the Accomplishment 

Instructions of Boeing Service Bulletin 737– 

28–1241, dated April 7, 2006, are acceptable 

for compliance with the requirements of 

paragraph (g)(2) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, ATTN: 

Stephen Oshiro, Aerospace Engineer, 

Systems and Equipment Branch, ANM–130S, 

FAA, Seattle ACO, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6480; fax (425) 917–6590; has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. 

(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 appropriate principal inspector 

(PI) in the FAA Flight Standards District 

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

FSDO. 

Material Incorporated by Reference 

(k) You must use Boeing Service Bulletin 

737–28–1241, Revision 1, dated August 31, 

2007; and Boeing Alert Service Bulletin 737– 

33A1140, dated May 22, 2006; 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 Boeing Commercial 


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32426 Federal Register / Vol. 74, No. 129 / Wednesday, July 8, 2009 / Rules and Regulations 

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 or 425–227–1152. 

(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, WA, on June 11, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–15405 Filed 7–7–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0446; Directorate 

Identifier 2009–CE–024–AD; Amendment 

39–15960; AD 2009–14–10] 

RIN 2120–AA64 

Airworthiness Directives; EADS–PZL 

‘‘Warszawa-Oke ̨cie’’ S.A. Model PZL– 

104 WILGA 80 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

issued 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: 

An inspection of a PZL–104 aeroplane that 

had a relatively long operational background 

revealed a severe corrosion of the steel front 

fuselage structural elements. 

It is likely that such corrosion can also be 

present on other aeroplanes of similar design 

and operational history. 

If left uncorrected, this condition could 

lead to loss of strength of the structural front 

posts elements and consequent reduction of 

the structural strength of the aeroplane. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

August 12, 2009. 

On August 12, 2009, the Director of 

the Federal Register approved the 

incorporation by reference of PZL–104 

Wilga 80 Maintenance Manual, pages 5– 

4 and 25–10, dated April 7, 2009, listed 

in this AD. 

As of May 18, 2009 (74 FR 18979; 

April 27, 2009), the Director of the 

Federal Register approved the 

incorporation by reference of EADS– 

PZL ‘‘Warszawa-Oke ̨cie’’ S.A. 

Mandatory Bulletin No. 10409036, 

dated March 18, 2009, listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

Docket 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: 

Doug Rudolph, Aerospace Engineer, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4059; fax: (816) 329–4090. 

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 May 12, 2009 (74 FR 22127), 

and proposed to supersede AD 2009– 

09–04, Amendment 39–15890 (74 FR 

18979, April 27, 2009). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states that: 

An inspection of a PZL–104 aeroplane that 

had a relatively long operational background 

revealed a severe corrosion of the steel front 

fuselage structural elements. 

It is likely that such corrosion can also be 

present on other aeroplanes of similar design 

and operational history. 

If left uncorrected, this condition could 

lead to loss of strength of the structural front 

posts elements and consequent reduction of 

the structural strength of the aeroplane. 

For the reason stated above, this 

Airworthiness Directive (AD) mandates 

inspecting the fuselage front posts, repairing 

any corrosion found and replacing pads 

made of foam rubber by pads made of 

Neoprene to prevent water ingression. 

The Administrative Procedure Act 

does not permit including long-term 

requirements in an urgent safety of 

flight action where the rule becomes 

effective at the same time the public has 

the opportunity to comment. We 

analyzed the short-term action and the 

long-term actions of the MCAI 

separately to determine the necessity of 

public notice. Therefore, AD 2009–09– 

04 addressed the initial short-term 

inspection requirement of the MCAI, but 

we did not include the required longterm repetitive inspections in the 

immediately adopted rule. We proposed 

the long-term repetitive inspections in 

the NPRM to allow public comment. 

The NPRM retained the short-term 

initial inspection and proposed the 

mandatory long-term action of 

repetitively inspecting the fuselage front 

posts through a revision to the airplane 

maintenance program. 

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 

as proposed. 

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 FAA policies. 

Any such differences are highlighted in 

a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

26 products of U.S. registry. We also 

estimate that it will take about 50 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $80 per work-hour. 

Required parts will cost about $150 per 

product. 

Based on these figures, we estimate 

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

to be $107,900 or $4,150 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 10 work-hours and require parts 

costing $0, for a cost of $800 per 

product. We have no way of 


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