Federal Register / Vol. 74, No. 109 / Tuesday, June 9, 2009 / Proposed Rules 27257 

December 20, 2006, that corresponds to the 

general visual inspection specified in 

Goodrich ICA for Boeing Model 737–300/ 

400/500 Airplanes, Document T2007–0010– 

0101, Revision D, dated January 16, 2007. 

No Alternative Inspections/Checks, 

Inspection/Check Intervals, or CDCCLs 

(l) After accomplishing the actions 

specified in paragraphs (g) and (h) of this AD, 

no alternative inspections/checks, 

inspection/check intervals, or CDCCLs may 

be used unless the inspections/checks, 

intervals, or CDCCLs are approved as an 

Alternative Method of Compliance (AMOC) 

in accordance with the procedures specified 

in paragraph (m) of this AD. 

AMOCs 

(m)(1) The Manager, Boston 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: Marc 

Ronell, Aerospace Engineer, ANE–150, FAA, 

Boston Aircraft Certification Office, 12 New 

England Executive Park, Burlington, 

Massachusetts 01803; telephone (781) 238– 

7776; fax (781) 238–7170. 

(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. 

Issued in Renton, Washington, on June 2, 

2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–13494 Filed 6–8–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0522; Directorate 

Identifier 2008–NM–127–AD] 

RIN 2120–AA64 

Airworthiness Directives; 328 Support 

Services GmbH Dornier Model 328–100 

and –300 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 that would 

supersede an existing AD. 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: 

* * * A number of * * * rudder spring 

tab lever assemblies [of the rudder] were 

found cracked. 

This condition, if not corrected, could lead 

to failure of the rudder flight control system 

and consequent loss of control of the aircraft. 

* * * 

* * * * * 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by July 9, 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 

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

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact 328 Support 

Services GmbH, Global Support Center, 

P.O. Box 1252, D–82231 Wessling, 

Federal Republic of Germany; telephone 

+49 8153 88111 6666; fax +49 8153 

88111 6565; e-mail 

gsc.op@328support.de; Internet http:// 

www.328support.de. You may review 

copies of the referenced 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. 

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 proposed 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–2125; 

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–2009–0522; Directorate Identifier 

2008–NM–127–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 based on 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 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On April 26, 2004, we issued AD 

2004–09–16, Amendment 39–13605 (69 

FR 24953, May 5, 2004). (A correction 

of that AD was published in the Federal 

Register on May 12, 2004 (69 FR 

26434)). That AD required actions 

intended to address an unsafe condition 

on the products listed above. 

Since we issued AD 2004–09–16, we 

have determined that it is necessary to 

reduce the repetitive interval and 

require the replacement of certain 

rudder spring tab lever assemblies. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2008–0107, 

dated June 23, 2008 (referred to after 

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

condition for the specified products. 

The MCAI states: 

On 14 March 2002, an incident occurred 

with a Dornier 328–100 where the captain 

reported that the rudder was unresponsive. 

The aircraft landed without any further 

difficulties. A visual inspection of the rudder 

assembly was carried out and the spring tab 

assembly was found to be cracked and 

partially missing. During subsequent 

inspections of other aircraft, a number of 

additional rudder spring tab lever assemblies 

were found cracked. 

This condition, if not corrected, could lead 

to failure of the rudder flight control system 

27258 Federal Register / Vol. 74, No. 109 / Tuesday, June 9, 2009 / Proposed Rules 

and consequent loss of control of the aircraft. 

To address and correct this unsafe condition, 

LBA (Luftfahrt-Bundesamt) issued AD 2003– 

383 and 2003–384 [which correspond to FAA 

AD 2004–09–16] for the Dornier 328–100 and 

328–300 respectively, to require the initial 

and repetitive inspection of the rudder spring 

tab lever assembly and, in case cracks were 

found, the replacement of the rudder spring 

tab lever assembly with a serviceable unit. 

The current TC (type certificate) holder of 

this type design, 328 Support Services 

GmbH, has recently published Alert Service 

Bulletin ASB–328–27–036, Revision 2, which 

reduces the inspection interval to A-check 

[400 FH] (400 flight hours). In addition, 

Service Bulletin SB–328–27–459 was revised 

to change the compliance status from 

‘optional’ to ‘mandatory’ and instructs 

operators to replace the rudder spring tab 

lever assembly with an improved unit P/N 

(part number) 001A272A4020–004, ending 

the need for the repetitive inspections. 

For the reasons described above, this EASA 

AD retains the repetitive inspection 

requirements of LBA AD 2003–383, which is 

superseded, expands the applicability to all 

serial numbers, reduces the inspection 

interval to 400 [flight hours], and requires the 

replacement of the rudder spring tab lever 

assembly with an improved unit P/N 

001A272A4020–004, as specified in SB–328– 

27–459. 

The material used for the rudder 

spring tab lever assemblies on Model 

328–100 airplanes differs from the 

material used for the rudder spring tab 

lever assemblies on Model 328–300 

airplanes. Therefore, Model 328–300 

airplanes are not affected by the new 

requirements in this NPRM. You may 

obtain further information by examining 

the MCAI in the AD docket. 

Relevant Service Information 

328 Support Services GmbH has 

issued Dornier 328 Service Bulletin SB– 

328–27–459, Revision 2, dated February 

8, 2008; and Dornier 328 Alert Service 

Bulletin ASB–328–27–036, Revision 3, 

dated February 8, 2008. 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 Proposed 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 proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

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 proposed 

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 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 112 products of U.S. 

registry. 

The actions that are required by AD 

2004–09–16 and retained in this 

proposed AD affect 112 products of U.S. 

registry and take 1 work-hour per 

product, at an average labor rate of $80 

per work-hour. Based on these figures, 

the estimated cost of the currently 

required actions is $8,960, or $80 per 

product, per inspection cycle. 

We estimate that it would take about 

3 work-hours per product to comply 

with the new basic requirements of this 

proposed AD and it would affect 16 

products of U.S. registry. The average 

labor rate is $80 per work-hour. 

Required parts would cost about 

$12,861 per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these costs. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$209,616, or $13,101 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this 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 this 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

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 FAA amends § 39.13 by 

removing Amendment 39–13605 (69 FR 

24953, May 5, 2004), corrected at 69 FR 

26434, May 12, 2004, and adding the 

following new AD: 

328 Support Services GmbH (Formerly, 

AvCraft Aerospace GmbH, formerly 

Fairchild Dornier GmbH, formerly 

Dornier Luftfahrt GmbH): Docket No. 

FAA–2009–0522; Directorate Identifier 

2008–NM–127–AD. 

Federal Register / Vol. 74, No. 109 / Tuesday, June 9, 2009 / Proposed Rules 27259 

Comments Due Date 

(a) We must receive comments by July 9, 

2009. 

Affected ADs 

(b) The proposed AD supersedes AD 2004– 

09–16, Amendment 39–13605. 

Applicability 

(c) This AD applies to 328 Support 

Services GmbH Dornier Model 328–100 

airplanes on which a rudder spring tab lever 

assembly having part number 

001A272A4020–002 is installed, and all 

Model 328–300 airplanes. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

On 14 March 2002, an incident occurred 

with a Dornier 328–100 where the captain 

reported that the rudder was unresponsive. 

The aircraft landed without any further 

difficulties. A visual inspection of the rudder 

assembly was carried out and the spring tab 

assembly was found to be cracked and 

partially missing. During subsequent 

inspections of other aircraft, a number of 

additional rudder spring tab lever assemblies 

were found cracked. 

This condition, if not corrected, could lead 

to failure of the rudder flight control system 

and consequent loss of control of the aircraft. 

To address and correct this unsafe condition, 

LBA (Luftfahrt-Bundesamt) issued AD 2003– 

383 and 2003–384 [which correspond to FAA 

AD 2004–09–16] for the Dornier 328–100 and 

328–300 respectively, to require the initial 

and repetitive inspection of the rudder spring 

tab lever assembly and, in case cracks were 

found, the replacement of the rudder spring 

tab lever assembly with a serviceable unit. 

The current TC (type certificate) holder of 

this type design, 328 Support Services 

GmbH, has recently published Alert Service 

Bulletin ASB–328–27–036, Revision 2, which 

reduces the inspection interval to A-check 

[400 FH] (400 flight hours). In addition, 

Service Bulletin SB–328–27–459 was revised 

to change the compliance status from 

‘optional’ to ‘mandatory’ and instructs 

operators to replace the rudder spring tab 

lever assembly with an improved unit P/N 

(part number) 001A272A4020–004, ending 

the need for the repetitive inspections. 

For the reasons described above, this EASA 

AD retains the repetitive inspection 

requirements of LBA AD 2003–383, which is 

superseded, expands the applicability to all 

serial numbers, reduces the inspection 

interval to 400 [flight hours], and requires the 

replacement of the rudder spring tab lever 

assembly with an improved unit P/N 

001A272A4020–004, as specified in SB–328– 

27–459. 

Compliance 

(f) Required as indicated, unless 

accomplished previously. 

Restatement of Requirements of AD 2004– 

09–16, Including Repetitive Inspections With 

Reduced Intervals for Model 328–100 

Airplanes 

(g) For all airplanes: Within 400 flight 

hours or 2 months after June 9, 2004 (the 

effective date of AD 2004–09–16), whichever 

is first; do detailed and eddy current 

inspections for cracking of the bearing lugs 

of the rudder spring tab lever assembly by 

doing all the actions per Paragraphs 2.A., 

2.B., and 2.D. of the Accomplishment 

Instructions of Dornier Alert Service Bulletin 

ASB–328–27–036 (for Model 328–100 

airplanes), dated February 12, 2003, or 

Revision 3, dated February 8, 2008; or 

Dornier Alert Service Bulletin ASB–328J–27– 

013 (for Model 328–300 airplanes), dated 

February 12, 2003; as applicable. 

Note 1: For the purposes of this AD, a 

detailed inspection is defined as: ‘‘An 

intensive visual examination of a specific 

structural area, system, installation, or 

assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at intensity deemed appropriate by 

the inspector. Inspection aids such as mirror, 

magnifying lenses, etc., may be used. Surface 

cleaning and elaborate access procedures 

may be required.’’ 

(1) For Model 328–100 airplanes: If no 

cracking is found during any inspection 

required by paragraph (g) of this AD, do the 

next inspection within 400 flight hours after 

doing the last inspection, or within 400 flight 

hours after the effective date of this AD, 

whichever occurs later; and repeat the 

inspection thereafter at intervals not to 

exceed 400 flight hours. Repeat the 

inspections until the replacement required by 

paragraph (k) of this AD has been done. 

(2) For Model 328–300 airplanes: If no 

cracking is found during any inspection 

required by paragraph (g) of this AD, repeat 

the inspections thereafter at intervals not to 

exceed 24 months. 

Corrective Action 

(h) For all airplanes: If any cracking is 

found during any inspection required by 

paragraph (g) of this AD, do the applicable 

actions specified in paragraph (h)(1) or (h)(2) 

of this AD. 

(1) For Model 328–100 airplanes: Before 

further flight, do the replacement required by 

paragraph (k) of this AD, or replace the 

spring tab lever assembly with a new 

assembly by doing all the actions per 

Paragraph 2.C. of the Accomplishment 

Instructions of Dornier Alert Service Bulletin 

ASB–328–27–036, dated February 12, 2003, 

or Revision 3, dated February 8, 2008. 

(2) For Model 328–300 airplanes: Before 

further flight, replace the spring tab lever 

assembly with a new assembly by doing all 

the actions per Paragraph 2.C. of the 

Accomplishment Instructions of Dornier 

Alert Service Bulletin ASB–328J–27–013, 

dated February 12, 2003. Repeat the 

inspections required by paragraph (g) of this 

AD thereafter at intervals not to exceed 24 

months. 

Note 2: For Model 328–300 airplanes: 

There is no terminating action available for 

the repetitive inspections required by this 

AD. 

(i) Dornier Alert Service Bulletins ASB– 

328–27–036, dated February 12, 2003, and 

Revision 3, dated February 8, 2008; and 

ASB–328J–27–013, dated February 12, 2003; 

recommend reporting crack findings and 

returning damaged lever assemblies to the 

manufacturer, but this AD does not contain 

such requirements. 

New Requirements of This AD: Actions and 

Compliance 

(j) For Model 328–100 airplanes: As of the 

effective date of this AD, Dornier Alert 

Service Bulletin ASB–328–27–036, Revision 

3, dated February 8, 2008, must be used for 

accomplishing the inspections and corrective 

actions required by paragraphs (g) and (h) of 

this AD. 

(k) For Model 328–100 airplanes: Within 6 

months after the effective date of this AD, 

replace any rudder spring tab lever assembly 

having P/N 001A272A4020–002 with an 

improved unit having P/N 001A272A4020– 

004, in accordance with the Accomplishment 

Instructions of Dornier 328 Service Bulletin 

SB–328–27–459, Revision 2, dated February 

8, 2008. Accomplishment of the replacement 

required by this paragraph terminates the 

repetitive inspections required by paragraph 

(g)(1) of this AD. 

(l) Actions done before the effective date of 

this AD in accordance with Dornier 328 

Service Bulletin SB–328–27–459, dated May 

3, 2004; or Revision 1, dated January 24, 

2008, are acceptable for compliance with the 

corresponding requirements of this AD for 

Model 328–100 airplanes. Actions done 

before the effective date of this AD in 

accordance with Dornier Alert Service 

Bulletin ASB–328–27–036, Revision 1, dated 

May 7, 2004; or Revision 2, dated January 24, 

2008; are acceptable for compliance with the 

corresponding requirements of this AD for 

Model 328–300 airplanes. 

FAA AD Differences 

Note 3: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(m) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): 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: Dan Rodina, 

Aerospace Engineer, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2125; fax (425) 227–1149. 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. 

(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. 

27260 Federal Register / Vol. 74, No. 109 / Tuesday, June 9, 2009 / Proposed Rules 

Corrective actions are considered FAAapproved 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, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(n) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2008– 

0107, dated June 23, 2008; German 

Airworthiness Directive 2003–384, dated 

November 13, 2003; Dornier 328 Alert 

Service Bulletin ASB–328–27–036, Revision 

3, dated February 8, 2008; and Dornier 328 

Service Bulletin SB–328–27–459, Revision 2, 

dated February 8, 2008; for related 

information. 

Issued in Renton, Washington, on June 2, 

2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–13495 Filed 6–8–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0515; Directorate 

Identifier 2008–NM–071–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Model F.28 Mark 0070 and 0100 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: 

Following a red illuminated ‘‘DOOR NOT 

LOCKED’’ status light indication on the door 

lock indication panel after lift off, the cabin 

crew operated the door lock handle. This 

resulted in inadvertent opening of the 

downward opening passenger door in 

flight. * * * 

After inspection, it was found that the false 

red light might be the result of an incorrect 

clearance between lever Part Number (P/N) 

A26997–003 and the Up-Limit Switch. If the 

Up-Limit Switch has an incorrect clearance, 

the combination with cabin differential 

pressure build-up after lift-off might result in 

a false steady illuminating red ‘‘DOOR NOT 

LOCKED’’ indication on the Door Indication 

Panel. * * * 

* * * * * 

The unsafe condition is inadvertent 

opening of the door lock handle in 

flight, which could result in rapid 

decompression of the airplane or 

ejection of a passenger or crewmember 

through the door. The proposed AD 

would require actions that are intended 

to address the unsafe condition 

described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by July 9, 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. 

For service information identified in 

this proposed AD, contact Fokker 

Services B.V., Technical Services Dept., 

P.O. Box 231, 2150 AE Nieuw-Vennep, 

the Netherlands; telephone +31 (0)252– 

627–350; fax +31 (0)252–627–211; email technicalservices.fokkerservices@

stork.com; Internet http://www.myfok

kerfleet.com You may review copies of 

the referenced 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. 

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 proposed 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: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1137; 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–2009–0515; Directorate Identifier 

2008–NM–071–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 based on 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 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agency 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2008–0020, 

dated January 28, 2008 (referred to after 

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

condition for the specified products. 

The MCAI states: 

Following a red illuminated ‘‘DOOR NOT 

LOCKED’’ status light indication on the door 

lock indication panel after lift off, the cabin 

crew operated the door lock handle. This 

resulted in inadvertent opening of the 

downward opening passenger door in flight. 

It appeared that the cabin crew was unaware 

of the content of Fokker 70/100 Service Letter 

(SL) 272. This SL informs not to operate the 

door lock handle after the aircraft has started 

to move or before it has come to a complete 

standstill. 

After inspection, it was found that the false 

red light might be the result of an incorrect 

clearance between lever Part Number (P/N) 

A26997–003 and the Up-Limit Switch. If the 

Up-Limit Switch has an incorrect clearance, 

the combination with cabin differential 

pressure build-up after lift-off might result in 

a false steady illuminating red ‘‘DOOR NOT 

LOCKED’’ indication on the Door Indication 

Panel. The original Fokker Service Bulletin 

SBF100–52–044 and the associated Aircraft 

Maintenance Manual (AMM) task mentioned 

a clearance of 1,3 mm ± 0,3 mm. Later, based 

on a trial, an improved clearance of 0,3 mm 

± 0,2 mm was introduced. Both documents 

have been revised for that reason. Later 

production serial number aircraft with