5692 Federal Register / Vol. 75, No. 23 / Thursday, February 4, 2010 / Rules and Regulations 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2010–03–04 PIAGGIO AERO INDUSTRIES 

S.p.A.: Amendment 39–16187; Docket 

No. FAA–2009–1081; Directorate 

Identifier 2009–CE–058–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective March 11, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model PIAGGIO 

P–180 airplanes, all serial numbers through 

1180, certificated in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 24: Electric Power. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

An operator reported a short circuit 

between a generator power cable and an antiice shutoff valve, which was caused by 

chafing between the cable and the valve; the 

insulation of the cable and surrounding 

sleeve were worn off. 

An investigation revealed that a scarce 

clearance between the cables and adjacent 

parts, together with vibrations of generator 

power cables favoured by insufficient 

clamping, was the root cause of the damage. 

If left uncorrected, this situation could lead 

to short circuits with possible fire and/or loss 

of important aircraft systems. 

This Airworthiness Directive (AD) requires 

an inspection to detect damaged cables/ 

sleeves, and replacement/repair as necessary; 

in addition, this AD requires to ensure that 

acceptable minimum clearances between 

cables and parts exist, and to improve 

clamping to minimize vibrations of the 

cables. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Within 3 months after March 11, 2010 

(the effective date of this AD), inspect for 

minimum clearance and insulation damage 

to the generator power cables in accordance 

with Part A of the ACCOMPLISHMENT 

INSTRUCTIONS of PIAGGIO AERO 

INDUSTRIES S.p.A. Service Bulletin 

(Mandatory) N.: 80–0271, dated May 18, 

2009. 

(2) If, as a result of the inspection required 

by paragraph (f)(1) of this AD, any 

discrepancy (inadequate clearance or 

insulation damage) is found, before further 

flight, do all necessary corrective actions in 

accordance with Part B of the 

ACCOMPLISHMENT INSTRUCTIONS of 

PIAGGIO AERO INDUSTRIES S.p.A. Service 

Bulletin (Mandatory) N.: 80–0271, dated May 

18, 2009. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

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: Sarjapur Nagarajan, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4145; fax: (816) 

329–4090. 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. 

(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 

(h) Refer to MCAI European Aviation 

Safety Agency AD No.: 2009–0212, dated 

October 6, 2009; and PIAGGIO AERO 

INDUSTRIES S.p.A. Service Bulletin 

(Mandatory) N.: 80–0271, dated May 18, 

2009, for related information. 

Material Incorporated by Reference 

(i) You must use PIAGGIO AERO 

INDUSTRIES S.p.A. Service Bulletin 

(Mandatory) N.: 80–0271, dated May 18, 

2009, 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 Piaggio Aero Industries 

S.p.a., Via Cibrario, 4—16154 Genoa, Italy; 

telephone +39 010 06481 741; fax: +39 010 

6481 309; Internet: http:// 

www.piaggioaero.com, or e-mail: 

MMicheli@piaggioaero.it. 

(3) You may review copies of the service 

information incorporated by reference for 

this AD at the FAA, Central Region, Office of 

the Regional Counsel, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the Central 

Region, call (816) 329–3768. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD 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 Kansas City, Missouri, on January 

21, 2010. 

James E. Jackson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–1691 Filed 2–3–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0608; Directorate 

Identifier 2008–NM–215–AD; Amendment 

39–16188; AD 2010–03–05] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–200C and –200F 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Model 747–200C and –200F series 

airplanes. This AD requires a high 

frequency eddy current (HFEC) 

inspection for cracks of certain fastener 

holes, and corrective action if necessary. 

This AD also requires repetitive 

replacements of the upper chords, straps 

(or angles), and radius fillers of certain 

upper deck floor beams, and, for any 

replacement that is done, detailed and 

open-hole HFEC inspections for cracks 

of the modified upper deck floor beams, 

and corrective actions if necessary. This 

AD results from a report from the 

manufacturer that the accomplishment 

of certain existing inspections, repairs, 

and modifications is not adequate to 

ensure the structural integrity of the 

affected 7075 series aluminum alloy 

upper deck floor beam upper chords on 

airplanes that have exceeded certain 

thresholds. We are issuing this AD to 

prevent cracking of the upper chords 

and straps (or angles) of the floor beams, 

which could lead to failure of the floor 

beams and consequent loss of 

controllability, rapid decompression, 

and loss of structural integrity of the 

airplane. 

DATES: This AD is effective March 11, 

2010. 

The Director of the Federal Register 

approved the incorporation by reference 


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Federal Register / Vol. 75, No. 23 / Thursday, February 4, 2010 / Rules and Regulations 5693 

of a certain publication listed in the AD 

as of March 11, 2010. 

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: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6437; 

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 all 

Model 747–200C and –200F series 

airplanes. That NPRM was published in 

the Federal Register on July 6, 2009 (74 

FR 31894). That NPRM proposed to 

require a high frequency eddy current 

inspection for cracks of certain fastener 

holes, and corrective action if necessary. 

That NPRM also proposed to require 

repetitive replacements of the upper 

chords, straps (or angles), and radius 

fillers of certain upper deck floor beams, 

and, for any replacement that is done, 

detailed and open-hole HFEC 

inspections for cracks of the modified 

upper deck floor beams, and corrective 

actions if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received from 

the commenters. 

Support for the NPRM 

One commenter, Boeing, agrees with 

the contents of the NPRM. 

Request To Clarify Compliance Time of 

Modification 

One commenter, Northwest Airlines 

(NWA), requests that we clarify whether 

the modification that is mandated by 

paragraph (g) of AD 2005–07–21, 

Amendment 39–14046 (70 FR 18277, 

April 11, 2005), is required during the 

accomplishment of the initial 15,000- 

flight-cycle post-upper chord 

replacement inspection proposed by the 

NPRM. NWA notes that the NPRM 

would require replacing the upper deck 

floor beam upper chords before the 

accumulation of 21,000 total flight 

cycles, or within 1,500 flight cycles after 

the effective date of the AD, whichever 

is later. NWA also states that the 

proposed rule would mandate 

inspecting the upper deck floor beams 

within 15,000 flight cycles after 

replacement of the upper chords. NWA 

notes that the inspections are to be 

completed in accordance with the 

Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2429, 

Revision 2, dated October 16, 2008; and 

Boeing Alert Service Bulletin 747– 

53A2439, Revision 2, dated July 17, 

2008. NWA notes that inspections per 

Boeing Alert Service Bulletins 747– 

53A2429 and 747–53A2439 were 

previously mandated. NWA points out 

that the Manager of the Seattle Aircraft 

Certification Office has previously 

approved the accomplishment of the 

applicable inspection, repair, and 

modification procedures contained in 

Boeing Alert Service Bulletin 747– 

53A2696, dated October 16, 2008, as an 

alternative method of compliance 

(AMOC) for paragraphs (f) and (g) of AD 

2006–08–02, Amendment 39–14556 (71 

FR 18618, April 12, 2006), and the 

inspection, repair, and modification 

requirements of paragraphs (a), (b), (c), 

(e), (g)(1), (h)(2), (i), (j), (k), and (l) of AD 

2005–07–21. 

We agree to provide clarification of 

the post-upper chord replacement 

actions. Paragraph (h) of this final rule 

requires detailed and HFEC inspections 

for cracks of the modified upper deck 

floor beams, in accordance with the 

Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2696, 

dated October 16, 2008, within 15,000 

flight cycles after the upper chord 

replacement, or within 1,500 flight 

cycles after the effective date of this AD, 

whichever occurs later. In addition, 

paragraph (h) of this final rule requires 

a repeat accomplishment of the upper 

chord replacement within 6,000 flight 

cycles after doing the initial post-upper 

chord replacement inspections. Boeing 

Alert Service Bulletin 747–53A2696 in 

turn refers to Boeing Alert Service 

Bulletins 747–53A2429, Revision 2; and 

747–53A2439, Revision 2; for inspection 

procedures only. Therefore, the 

modification in accordance with Boeing 

Alert Service Bulletin 747–53A2429, 

dated March 22, 2001, as mandated by 

paragraph (g) of AD 2005–07–21, is not 

required by this final rule. Operators 

should note that accomplishment of the 

actions per this AD has been approved 

as an AMOC to the corresponding 

requirements of AD 2005–07–21 and AD 

2006–08–02 as described above. We 

have not changed the final rule in regard 

to this issue. 

Explanation of Changes Made to This 

AD 

We have revised this AD to identify 

the legal name of the manufacturer as 

published in the most recent type 

certificate data sheet for the affected 

airplane models. 

Boeing Commercial Airplanes has 

received an Organization Designation 

Authorization (ODA), which replaces 

their previous designation as a 

Delegation Option Authorization (DOA) 

holder. We have revised paragraph (j)(3) 

of this AD to delegate the authority to 

approve an alternative method of 

compliance for any repair required by 

this AD to the Boeing Commercial 

Airplanes ODA. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, 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. 

Costs of Compliance 

We estimate that this AD affects 25 

airplanes of U.S. registry. The following 

table provides the estimated costs for 

U.S. operators to comply with this AD. 


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5694 Federal Register / Vol. 75, No. 23 / Thursday, February 4, 2010 / Rules and Regulations 

TABLE—ESTIMATED COSTS

Work hours 

Average 

labor rate 

per hour 

Parts Cost per product 

Number of 

U.S.- 

registered 

airplanes 

Fleet cost 

663 ............... $80 None ............ $53,040 per inspection/replacement 

cycle.

25 $1,326,000 per inspection/replacement 

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 

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: 

2010–03–05 The Boeing Company: 

Amendment 39–16188. Docket No. 

FAA–2009–0608; Directorate Identifier 

2008–NM–215–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective March 11, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all The Boeing 

Company Model 747–200C and –200F series 

airplanes, certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from a report from the 

manufacturer that the accomplishment of 

certain existing inspections, repairs, and 

modifications is not adequate to ensure the 

structural integrity of the affected 7075 series 

aluminum alloy upper deck floor beam upper 

chords on airplanes that have exceeded 

certain thresholds. We are issuing this AD to 

prevent cracking of the upper chords and 

straps (or angles) of the floor beams, which 

could lead to failure of the floor beams and 

consequent loss of controllability, rapid 

decompression, and loss of structural 

integrity of the airplane. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Initial Inspection and Replacement 

(g) Before the accumulation of 21,000 total 

flight cycles, or within 1,500 flight cycles 

after the effective date of this AD, whichever 

occurs later: Do an open-hole high frequency 

eddy current (HFEC) inspection of all the 

fastener holes accessed for upper chord 

removal for cracks, and replace the upper 

chords, straps (or angles), and radius fillers 

of the upper deck floor beams, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2696, 

dated October 16, 2008. 

Repetitive Replacements and PostReplacement Inspections 

(h) Within 15,000 flight cycles after doing 

the replacement required by paragraph (g) of 

this AD, or within 1,500 flight cycles after the 

effective date of this AD, whichever occurs 

later: Do detailed and HFEC inspections for 

cracks of the modified upper deck floor 

beams, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2696, dated October 

16, 2008. Within 6,000 flight cycles after 

doing the detailed and HFEC inspections, 

repeat the replacement specified in 

paragraph (g) of this AD. Repeat the postreplacement inspections and replacement at 

the applicable times specified in paragraph 

1.E. of Boeing Alert Service Bulletin 747– 

53A2696, dated October 16, 2008. 

Repair of Cracks 

(i) If any crack is found during any 

inspection required by this AD: Before 

further flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (j) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(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: Ivan 

Li, Airframe Branch, ANM–120S, FAA, 

Seattle ACO, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6437; fax (425) 917–6590. Or, 

e-mail information to 9-ANM-Seattle-ACOAMOC-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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 


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Federal Register / Vol. 75, No. 23 / Thursday, February 4, 2010 / Rules and Regulations 5695 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

Material Incorporated by Reference 

(k) You must use Boeing Alert Service 

Bulletin 747–53A2696, dated October 16, 

2008, 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 

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, Washington, on January 

21, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–1690 Filed 2–3–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1116; Directorate 

Identifier 2009–CE–061–AD; Amendment 

39–16193; AD 2010–03–09] 

RIN 2120–AA64 

Airworthiness Directives; PIAGGIO 

AERO INDUSTRIES S.p.A Model 

PIAGGIO P–180 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) 

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: 

Cracks have been detected on the upper 

flange (cap) of several ‘‘0’’ pressure bulkheads 

on the production line; none of the cracks 

had spread across the thickness of material. 

Investigation revealed that all ‘‘0’’ pressure 

bulkheads installed on aircraft from MSN 

1106 up to 1189 could have the same cracks. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

March 11, 2010. 

On March 11, 2010, the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at 

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: 

Sarjapur Nagarajan, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4145; 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 November 30, 2009 (74 FR 

62516). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Cracks have been detected on the upper 

flange (cap) of several ‘‘0’’ pressure bulkheads 

on the production line; none of the cracks 

had spread across the thickness of material. 

Investigation revealed that all ‘‘0’’ pressure 

bulkheads installed on aircraft from MSN 

1106 up to 1189 could have the same cracks. 

Although calculations confirm the low 

stress level in that area, a reinforcement of 

the ‘‘0’’ pressure bulkhead is suggested to 

avoid crack growth and the eventual failure 

of the bulkhead. 

For the reasons stated above, this new 

Airworthiness Directive (AD) mandates a 

non-destructive inspection and a 

reinforcement—by installation of doublers— 

of the ‘‘0’’ pressure bulkhead. This AD also 

includes a reporting requirement of the 

inspection results. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Mr. Carlo Cardu of Piaggio Aero 

Industries states that he understands 

owners/operators may comply with an 

AD before the specified compliance 

time; however, he also states it would be 

best for the owners/operators of the 

airplanes affected by this AD to do the 

inspection and modification of the 

pressure bulkhead during a D 

inspection, which is at 3,000 hours 

time-in-service (TIS). 

Mr. Cardu requests changing the 

compliance time for the inspection and 

modification from ‘‘when the airplane 

reaches a total of 3,600 hours TIS 

***’’ to ‘‘before the airplane reaches a 

total of 3,600 hours TIS * * *.’’ 

We agree with the intent of the 

commenter. To make it clear that the 

owners/operators of the airplanes 

affected by this AD may comply with 

the AD before their airplane reaches 

3,600 hours TIS, we will change the 

compliance time in the final rule AD 

action to allow the inspection and 

modification to be done before or when 

the airplane reaches a total of 3,600 

hours TIS or within the next 30 days 

after the effective date of the AD, 

whichever occurs later. 

Conclusion 

We reviewed the available data, 

including the comment received, 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 FAA policies. 

Any such differences are highlighted in 

a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

63 products of U.S. registry. We also 

estimate that it would take about 120 


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