AD 70-19-01

AD Final Rules - DRS_70-19-01.html
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AD Number:
70-19-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Airplanes
Subject:
Auxiliary Engine Starting System
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
11/13/1970
Make:
The Boeing Company
Model:
DC-8-11 | DC-8-12 | DC-8-21 | DC-8-31 | DC-8-32 | DC-8-33 | DC-8-41 | DC-8-42 | DC-8-43 | DC-8-51 | ...Show more
Product Type:
Aircraft
Product Subtype:
Large Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 70-19-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-1107

AD NUMBER:   70-19-01

SUBJECT HEADING:   Airworthiness Directives; MCDONNELL DOUGLAS DC-8 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective November 13, 1970.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
70-19-01 MCDONNELL DOUGLAS: Amdt. 39-1079 as amended by Amendment 39-1107. Applies to all McDonnell Douglas Model DC-8 airplanes equipped with the high pressure air auxiliary engine starting system. Within the next 50 hours time in service after the effective date of this AD, unless already accomplished, deactivate the high pressure air storage system in the auxiliary engine starting system in accordance with McDonnell Douglas All Operators Telegraphic Maintenance Campaign No. C1-SVC-DC8-COM-21, dated August 13, 1970, and/or Supplement C1-SVC-DC8-COM-22, dated August 14, 1970, or an equivalent procedure approved by the Chief, Aircraft Engineering Division.

To reactivate the auxiliary engine starting system high pressure air storage system, accomplish the following as applicable:

(a) For all aircraft which have complied with McDonnell Douglas DC-8 Service Bulletin 80-15, dated August 28, 1970, remove the protective coating which was installed within the air chambers per Section 2.E(1)(a) and 2.E(1)(c) of Option I and/or Section 2.G of Option II of the Service Bulletin.

(b) Visually and ultrasonically inspect the MLG strut air storage chambers in accordance with McDonnell Douglas DC-8 Service Bulletin 80-15, Paragraph 2.D and Paragraph 2.E(3), dated August 28, 1970, or later FAA approved revision or an equivalent inspection procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region.

If no cracks or corrosion are found in either MLG strut air storage chamber, the air storage system may be reactivated. If cracks or corrosion are found in either air chamber, the reactivation of the air storage system must be held in abeyance until the strut is overhauled in accordance with the McDonnell Douglas DC-8 Overhaul Manual or other FAA approved procedures.

(c) For all DC-8-62, -62F, -63, and -63F airplanes with the auxiliary spherical air reservoir, P/N 7755213-1, prior to reactivation, visually inspect the reservoir per McDonnell Douglas All Operators Letter AOL 8-476 (C1-7-92/TS/JED), dated September 22, 1970, or an equivalent inspection procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region. If corrosion is found in the reservoir, it must be replaced prior to reactivation of the system.

(d) Following reactivation of the air start system, the chemical air dryer cartridge must be replaced with a new cartridge at intervals not to exceed 25 hours of compressor operation and whenever the water separator malfunctions. To determine compressor operation time, the compressor must be controlled manually and a record of time of operation must be maintained. A placard shall be installed adjacent to the air compressor control and water separator circuit breaker on the electrical power center panel (28V DC Buss #4) which requires the flight crew to record the compressor operation time in the aircraft log.

As an alternate procedure to manual compressor regulation and operating time recording, the air start compressor system may be returned to normal automatic operation, provided the chemical air dryer cartridge is replaced at intervals not to exceed 250 flight hours.

(e) Water separator operation, for those airplanes so equipped, must be checked at intervals not to exceed 250 flight hours. A minimum of three overboard water discharge cycles at five to eight minute intervals indicates satisfactory water separator functioning. Unsatisfactory water separator operation must be rectified prior to further operation of the aircraft with the pressurized air start system activated. The air start system may be temporarily deactivated by opening and securing the air compressor control and water separator circuit breaker on the electrical power center panel (28V DC Buss #4), or any equivalent FAA approved procedure. To preserve the integrity of the air start system, the aircraft must not be operated for more than 50 flight hours with both unsatisfactory water separator operation and a temporarily deactivated air start system.

NOTE: Paragraphs (d) and (e) apply to only those aircraft utilizing the onboard air start compressor system.

(f) At intervals not to exceed 1200 flight hours, visually inspect the interior of each air chamber for the presence of water. If water is found, repeat Section (b), above.

(g) When a ground source is used for recharging the air storage system or for direct engine start on the air combustion system, use dry air having a dew point of -65 degrees F or lower. For airplanes with the Hi-low starting system, use of dry nitrogen as an alternate to dry air is satisfactory.

Amendment 39-1079 effective September 15, 1970, and was effective upon receipt for all recipients of the telegram dated August 21, 1970, which contained this amendment.

This Amendment 39-1107 becomes effective November 13, 1970.


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