Federal Register / Vol. 73, No. 27 / Friday, February 8, 2008 / Proposed Rules 7489 

cost of this proposed AD to the U.S. 

operators to be between $560,880 and 

$747,840, or between $720 and $960 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. 

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, 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 adding 

the following new AD: 

Boeing: Docket No. FAA–2008–0149; 

Directorate Identifier 2007–NM–319–AD. 

Comments Due Date 

(a) We must receive comments by March 

24, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model 737–100, 

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

airplanes, certificated in any category; as 

identified in Boeing Alert Service Bulletin 

737–38A1054, dated August 23, 2007. 

Unsafe Condition 

(d) This AD results from a report of a 

separated hose assembly for the passenger 

water system. We are issuing this AD to 

prevent a water leak into the flight deck 

ceiling, which could result in an electrical 

short and possible loss of several functions 

essential to safe flight. 

Compliance 

(e) Comply with this AD within the 

compliance times specified, unless already 

done. 

Replacement 

(f) Within 60 months after the effective 

date of this AD, replace the existing straightto-90-degree hose assembly for the Lavatory 

‘‘A’’ water supply with a new straight hose 

assembly and a separate 90-degree elbow 

fitting, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–38A1054, dated August 

23, 2007. 

Parts Installation 

(g) As of the effective date of this AD, any 

hose assembly part having a part number 

identified in Table 1 of this AD must not be 

used in any location that is subject to the 

requirements of this AD. However, those 

parts may be used in other locations if not 

otherwise prohibited. 

TABLE 1.—SPARE PARTS PROHIBITED FOR THIS AD 

Airplane group identified in Boeing Alert Service Bulletin 737–38A1054, 

dated August 23, 2007 Existing part Nos. 

1 and 2 ..................................................................................................... 10–61998–430, AS4471–08–0401, or AS4471–08–0404. 

3 ................................................................................................................ 10–61998–25 or 10–60871–125. 

4 ................................................................................................................ 10–61998–31 or 10–60871–139. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, ATTN: 

Marcia Smith, Aerospace Engineer, Cabin 

Safety and Environmental Systems Branch, 

ANM–150S, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

917–6484; 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. 

Issued in Renton, Washington, on January 

31, 2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–2353 Filed 2–7–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0151; Directorate 

Identifier 2007–NM–347–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 727 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 


ebenthall on PRODPC61 with PROPOSALS
7490 Federal Register / Vol. 73, No. 27 / Friday, February 8, 2008 / Proposed Rules 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Boeing Model 727 airplanes. This 

proposed AD would require repetitive 

inspections for any crack in the area of 

the elevator side fitting/hinge fitting 

joint and for any crack or elongation 

inside and outside of the holes in the 

clevis and in the lug, corrective actions 

if necessary, and other specified actions. 

This proposed AD results from reports 

of elongated holes and cracks found in 

the lugs of the attachment fittings of the 

elevator quadrant upper support 

assembly at the tip of the vertical fin. 

We are proposing this AD to detect and 

correct damage to the aft attachment 

lugs of the elevator quadrant support 

assembly that could lead to failure of 

the lugs. This condition could accelerate 

wear elsewhere in the elevator control 

system, which could reduce the crew’s 

ability to maintain safe flight. 

DATES: We must receive comments on 

this proposed AD by March 24, 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 Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207. 

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: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6577; fax (425) 917–6590. 

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–2008–0151; Directorate Identifier 

2007–NM–347–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 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We have received reports of elongated 

holes or cracks found in the lugs of the 

attachment fittings on three Boeing 

Model 727 airplanes. The attachment 

fittings are located on the left and right 

sides of the elevator quadrant upper 

support assembly at the tip of the 

vertical fin. In one incident, the lug was 

cracked completely through. The 

airplanes had accumulated between 

28,385 and 72,448 total flight hours and 

between 16,387 and 47,485 total flight 

cycles. Damage to the aft attachment 

lugs of the elevator quadrant support 

assembly could lead to failure of the 

lugs. This condition, if not corrected, 

could accelerate wear elsewhere in the 

elevator control system, which could 

reduce the crew’s ability to maintain 

safe flight. 

Relevant Service Information 

We have reviewed Boeing Special 

Attention Service Bulletin 727–55–

0092, dated June 4, 2007. Part 2 of the 

Accomplishment Instructions of the 

service bulletin describes procedures for 

doing repetitive detailed inspections for 

any crack in the area of the elevator side 

fitting/hinge fitting joint, repetitive 

detailed inspections for elongation 

inside and outside of the holes in the 

clevis and in the lug, and high 

frequency eddy current (HFEC) 

inspections for any crack inside and 

outside of the holes in the clevis and in 

the lug. The service bulletin specifies 

doing these initial inspections within 18 

months of the date on the service 

bulletin. The service bulletin also 

specifies repeating the inspections at 

intervals not to exceed 24 months, 4,000 

flight hours, or 3,000 flight cycles, 

whichever occurs first, until the repair 

or modification specified in Part 3 of the 

Accomplishment Instructions is done. 

The service bulletin also describes 

procedures for doing corrective actions 

if necessary. The corrective actions, 

which the service bulletin specifies 

doing before further flight, include the 

following actions: 

• Repairing the elevator side fittings 

and hinge fittings as specified in Part 3 

of the Accomplishment Instructions if 

any crack, or any hole diameter 

elongation over 0.3203 inch, is found 

during the inspections specified in Part 

2 of the service bulletin. The repair 

includes oversizing the holes, 

fabricating new bushings, installing and 

in-line reaming the fabricated bushings 

through the entire stack-up, and 

installing the elevator side fittings. 

• Replacing the bushings with 

fabricated bushings if any hole diameter 

elongation over 0.3203 inch is found 

during the inspections specified in Part 

4 of the Accomplishment Instructions of 

the service bulletin. 

• Contacting Boeing for repair 

instructions if any damage is beyond the 

repair limits or any crack is found in the 

area of the elevator side fitting/hinge 

fitting joint, during any inspection 

specified in Part 2 or Part 4 of the 

Accomplishment Instructions of the 

service bulletin. 

The service bulletin also describes 

procedures for doing other specified 

actions, which include the following: 

• Either installing the elevator side 

fittings and access panels and restoring 

the cable tension, or modifying the 

elevator side fittings and hinge fittings, 

if all of the holes are found acceptable 

during the inspections specified in Part 

2 of the Accomplishment Instructions. 

The modification includes oversizing 

the holes, fabricating and installing new 

bushings, in-line reaming the fabricated 

bushings through the entire stack-up, 

and installing the elevator side fittings. 

The service bulletin specifies that the 

modification must be done in 

conjunction with the Part 2 detailed and 

HFEC inspections. 

• After the repair or modification 

specified in Part 3 of the 

Accomplishment Instructions has been 

done, doing repetitive detailed 

inspections for any crack in the area of 

the elevator side fitting/hinge fitting 

joint and repetitive detailed inspections 

for elongation inside and outside of the 

holes in the clevis and in the lug as 

specified in Part 4 of the 

Accomplishment Instructions. The 

service bulletin specifies doing the 


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Federal Register / Vol. 73, No. 27 / Friday, February 8, 2008 / Proposed Rules 7491 

initial inspections within 24,000 flight 

hours or 16,000 flight cycles, whichever 

occurs first, after accomplishing the 

repair or modification specified in Part 

3 of the service bulletin. The service 

bulletin also specifies repeating the 

inspections at intervals not to exceed 

24,000 flight hours or 16,000 flight 

cycles, whichever occurs first. 

FAA’s Determination and Requirements 

of This Proposed AD 

We are proposing this AD because we 

evaluated all relevant information and 

determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the(se) 

same type design(s). This proposed AD 

would require accomplishing the 

actions specified in the service 

information described previously, 

except as discussed under ‘‘Difference 

between the Proposed AD and Service 

Bulletin.’’

Difference Between the Proposed AD 

and Service Bulletin 

The service bulletin specifies to 

contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing those conditions in 

one of the following ways: 

• Using a method that we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by an 

Authorized Representative for the 

Boeing Commercial Airplanes 

Delegation Option Authorization 

Organization whom we have authorized 

to make those findings. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 401 airplanes of U.S. 

registry. We also estimate that it would 

take about 2 work-hours per product to 

comply with this proposed AD. The 

average labor rate is $80 per work-hour. 

Based on these figures, we estimate the 

cost of this proposed AD to the U.S. 

operators to be $64,160 or $160 per 

product, per inspection cycle. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We 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. 

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, 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 adding 

the following new AD: 

Boeing: Docket No. FAA–2008–0151; 

Directorate Identifier 2007–NM–347–AD. 

Comments Due Date 

(a) We must receive comments by March 

24, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Boeing Model 

727, 727C, 727–100, 727–100C, 727–200, and 

727–200F series airplanes, certificated in any 

category. 

Unsafe Condition 

(d) This AD results from reports of 

elongated holes and cracks found in the lugs 

of the attachment fittings of the elevator 

quadrant upper support assembly at the tip 

of the vertical fin. We are issuing this AD to 

detect and correct damage to the aft 

attachment lugs of the elevator quadrant 

support assembly that could lead to failure of 

the lugs. This condition could accelerate 

wear elsewhere in the elevator control 

system, which could reduce the crew’s 

ability to maintain safe flight. 

Compliance 

(e) Comply with this AD within the 

compliance times specified, unless already 

done. 

Repetitive Inspections and Corrective/Other 

Specified Actions 

(f) At the applicable compliance times 

specified in paragraph 1.E. of Boeing Special 

Attention Service Bulletin 727–55–0092, 

dated June 4, 2007, except as provided by 

paragraph (g) of this AD: Do the detailed 

inspection for any crack in the area of the 

elevator side fitting/hinge fitting joint, 

detailed inspections for elongation inside 

and outside of the holes in the clevis and in 

the lug, and high frequency eddy current 

(HFEC) inspections for any crack inside and 

outside of the holes in the clevis and in the 

lug, and do all the applicable corrective 

actions and other specified actions, by 

accomplishing all of the applicable actions 

specified in the Accomplishment 

Instructions of the service bulletin, except as 

provided by paragraph (h) of this AD. Repeat 

the inspections thereafter at the applicable 

intervals specified in paragraph 1.E. of the 

service bulletin. Accomplishing the repair or 

modification specified in Part 3 of the service 

bulletin only terminates the repetitive 

inspections specified in Part 2 of the service 

bulletin. 

Exception to Compliance Times 

(g) Where Boeing Special Attention Service 

Bulletin 727–55–0092, dated June 4, 2007, 

specifies counting the compliance time from 

‘‘* * * the date on this service bulletin,’’ this 

AD requires counting the compliance time 

from the effective date of this AD. 

Exception to Corrective Actions 

(h) If any damage beyond the repair limits 

or any crack is found in the area of the 

elevator side fitting/hinge fitting joint during 

any inspection required by this AD, and 

Boeing Special Attention Service Bulletin 

727–55–0092, dated June 4, 2007, specifies to 

contact Boeing for appropriate action: Before 

further flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (i) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Seattle Aircraft 

Certification Office, FAA, ATTN: Berhane 

Alazar, Aerospace Engineer, Airframe 

Branch, ANM–120S, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 


ebenthall on PRODPC61 with PROPOSALS
7492 Federal Register / Vol. 73, No. 27 / Friday, February 8, 2008 / Proposed Rules 

(425) 917–6577; 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. 

(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 an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has 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. 

Issued in Renton, Washington, on January 

31, 2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–2354 Filed 2–7–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0152; Directorate 

Identifier 2007–NM–348–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–400, –500, –600, –700, 

–700C, –800, and –900 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 certain 

Boeing Model 737–400, –500, –600, 

–700, –700C, –800, and –900 series 

airplanes. This proposed AD would 

require an inspection to determine the 

part and serial numbers of the 

windshield wiper motors for the pilot’s 

and first officer’s windshields, and the 

applicable corrective action. This 

proposed AD results from two reports 

that the left and right windshield wipers 

stopped working in flight. We are 

proposing this AD to prevent failure of 

the windshield wipers in wet weather, 

which could result in decreased 

visibility for the flightcrew. 

DATES: We must receive comments on 

this proposed AD by March 24, 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 Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207. 

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: Nick 

Wilson, Aerospace Engineer, Cabin 

Safety and Environmental Systems 

Branch, ANM–150S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6476; 

fax (425) 917–6590. 

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–2008–0152; Directorate Identifier 

2007–NM–348–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 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We have received two reports that the 

left and right windshield wipers 

stopped working in flight. In one 

incident, the left and right windshield 

wiper motors stopped at the same time 

during a landing approach in wet 

weather. Investigation revealed that the 

power converter module for the 

windshield wipers was not properly 

soldered. Failure of the windshield 

wipers in wet weather, if not corrected, 

could result in decreased visibility for 

the flightcrew. 

Other Related Rulemaking 

On October 2, 2003, we issued AD 

2003–20–13, amendment 39–13331 (68 

FR 58268, October 9, 2003), applicable 

to certain Boeing Model 737–400, –500, 

–600, –700, and –800 series airplanes. 

That AD requires either modification of 

the wiring to the windshield wiper 

motors in the flight compartment or 

replacement of those windshield wiper 

motor/converters with new motor/ 

converters. That AD resulted from 

reports of the windshield motors 

stalling during flight. We issued that AD 

to prevent a reduction in flightcrew 

visibility due to stalled wiper motors 

during heavy precipitation and a period 

of substantial crew workload, which 

could result in damage to the airplane 

structure and injury to flightcrew, 

passengers, or ground personnel during 

final approach for landing. For certain 

airplanes, accomplishing the 

modification required by paragraph (b) 

of AD 2003–20–13 is acceptable for 

compliance with certain requirements of 

this proposed AD. 

Relevant Service Information 

We have reviewed Boeing Service 

Bulletin 737–30A1057, Revision 1, 

dated October 31, 2007, for Model 737–

600, –700, –700C, –800, and –900 series 

airplanes; and Boeing Alert Service 

Bulletin 737–30A1059, dated September 

10, 2007, for Model 737–400 and –500 

series airplanes. The service bulletins 

describe procedures for looking at the 

windshield wiper motors for the pilot’s 

and first officer’s windshields to 

determine the part number and serial 

number of the windshield wiper motors, 

and doing the applicable corrective 

action. The corrective actions include 

the following: 

• Replacing the windshield wiper 

motor with an improved windshield 

wiper motor if the part and serial 

numbers cannot be read, or if the part 

and serial numbers are listed in 


ebenthall on PRODPC61 with PROPOSALS